Nachrichten für Luftfahrer 2013 Teil II (weicht ggf. von Druckversion ab)
intervals not to exceed 4,500 flight cycles until paragraph (i), (j)(1)(i), (j)(1)(ii), (k), (l), or (m) of this
AD has been done, as applicable. Although paragraph 1.D. of Boeing Alert Service Bulletin 737-
53A1210, Revision 1, dated October 25, 2001, references a reporting requirement, such reporting is
not required by this AD. Accomplishing the actions required by paragraph (p) or (q) of this AD ends
the repetitive requirements in this paragraph.
(h) Retained External Detailed Inspection With Reduced Compliance Time
This paragraph restates the requirements of paragraph (b) of AD 2004-18-06, Amendment 39-
13784 (69 FR 54206, September 8, 2004), with reduced compliance time and revised service
information. For all airplanes identified in Boeing Alert Service Bulletin 737-53A1210, Revision 1,
dated October 25, 2001: Before the accumulation of 40,000 total flight cycles, or within 4,500 flight
cycles after October 13, 2004 (the effective date of AD 2004-18-06), whichever is later, do an
external detailed inspection of the lower lobe area and section 41 of the fuselage for cracking, in
accordance with Part 2 and Figure 2 of the Work Instructions of Boeing Alert Service Bulletin 737-
53A1210, Revision 1, dated October 25, 2001; or in accordance with Part 4 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009; except
as provided by paragraph (o) of this AD. Repeat the inspection thereafter at intervals not to exceed
9,000 flight cycles until the actions specified in paragraph (j)(2) or paragraph (k), as applicable, of
this AD have been done. Accomplishing the actions required by paragraph (s) of this AD ends the
requirements in this paragraph.
(i) Retained Preventive Modification at Stringer 12
This paragraph restates the requirements of paragraph (c) of AD 2004-18-06, Amendment 39-
13784 (69 FR 54206, September 8, 2004), with revised service information. For Groups 3 and 5
airplanes identified in Boeing Alert Service Bulletin 737-53A1210, Revision 1, dated October 25,
2001: If no cracking is found during any inspection required by paragraph (g) of this AD, doing the
preventive modification of the chem-milled pockets in the upper skin, as specified in Part 5 of the
Work Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 1, dated October 25,
2001; or as specified in Part 7 of the Work Instructions of Boeing Alert Service Bulletin 737-
53A1210, Revision 3, dated July 16, 2009, except as required by paragraph (x) of this AD; ends the
repetitive external detailed and eddy current inspections required by paragraph (g) of this AD for the
modified area only. As of the effective date of this AD, use only Boeing Alert Service Bulletin 737-
53A1210, Revision 3, dated July 16, 2009, to do the actions required by this paragraph.
(j) Retained Corrective Actions
This paragraph restates the requirements of paragraph (d) of AD 2004-18-06, Amendment 39-
13784 (69 FR 54206, September 8, 2004), with revised service information. If any cracking is found
during any inspection required by paragraph (g), (h), (p), (q), or (s) of this AD, before further flight,
do the actions specified in paragraphs (j)(1) and (j)(2) of this AD, as applicable, in accordance with
the Work Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 1, dated October 25,
2001; or in accordance with the Work Instructions of Boeing Alert Service Bulletin 737-53A1210,
Revision 3, dated July 16, 2009. As of the effective date of this AD, use only Boeing Alert Service
Bulletin 737-53A1210, Revision 3, dated July 16, 2009, to do the actions required by this paragraph.
Where Boeing Alert Service Bulletin 737-53A1210, Revision 1, dated October 25, 2001; or Boeing
Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009; specify to contact Boeing for
repair instructions, before further flight, repair in accordance with a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA; or in accordance with data meeting the
type certification basis of the airplane if it is approved by the Boeing Commercial Airplanes
Organization Designation Authorization (ODA) or any other person authorized by the Manager,
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Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the
certification basis of the airplane and the approval must specifically refer to this AD.
(1) Except as provided by paragraph (k) of this AD, for cracking of the crown area, do the repair
specified in either paragraph (j)(1)(i) or (j)(1)(ii) of this AD.
(i) Do a time-limited repair in accordance with Part 4 of the Work Instructions of Boeing Alert
Service Bulletin 737-53A1210, Revision 1, dated October 25, 2001; or in accordance with Part 6 of
the Work Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16,
2009, except as required by paragraph (x) of this AD; then do the actions required by paragraph (l) of
this AD at the times specified in that paragraph. Installation of a time-limited repair ends the
repetitive inspections required by paragraph (g) of this AD for the repaired area only.
(ii) Do a permanent repair in accordance with Part 3 of the Work Instructions of Boeing Alert
Service Bulletin 737-53A1210, Revision 1, dated October 25, 2001; or in accordance with Part 5 of
the Work Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16,
2009. Installation of a permanent repair ends the repetitive inspections required by paragraph (g) of
this AD for the repaired area only. Installation of the lap joint repair specified in paragraph (g) of AD
2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002), is considered acceptable for
compliance with the corresponding permanent repair specified in this paragraph for the repaired areas
only.
(2) Except as provided by paragraph (k) of this AD, for cracking of the lower lobe area and
section 41, repair in accordance with Part 2 of the Work Instructions of Boeing Alert Service Bulletin
737-53A1210, Revision 1, dated October 25, 2001; or in accordance with paragraph (j)(2)(i) or
(j)(2)(ii) of this AD. Accomplishment of this repair ends the repetitive inspections required by
paragraph (h) of this AD for the repaired area only. As of the effective date of this, do the repair
specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
(i) Do a time-limited repair in accordance with Part 6 of the Work Instructions of Boeing Alert
Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009, except as required by paragraph (x)
of this AD, then do the actions required by paragraph (l) of this AD at the times specified in that
paragraph.
(ii) Do a permanent repair in accordance with Part 5 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009.
(k) Retained Optional Repair Method
This paragraph restates the requirements of paragraph (e) of AD 2004-18-06, Amendment 39-
13784 (69 FR 54206, September 8, 2004), with revised service information. For cracking in any area
specified in paragraphs (j)(1) and (j)(2) of this AD within the limitations of the applicable structural
repair manual (SRM) specified in paragraphs (k)(1) through (k)(4) of this AD, repair any cracks, in
accordance with a method approved by the Manager, Seattle ACO; or in accordance with data
meeting the type certification basis of the airplane if it is approved by the Boeing Commercial
Airplanes ODA or any other person authorized by the Manager, Seattle ACO, to make those findings.
For a repair method to be approved the repair must meet the certification basis of the airplane and the
approval must specifically refer to this AD. Accomplishment of the applicable repair terminates the
repetitive inspections required by paragraphs (g) and (h) of this AD for the repaired area only.
Guidance on repairing the cracking can be found in the applicable SRM specified in paragraphs
(k)(1) through (k)(4) of this AD.
(1) For Model 737-100, -200 series airplanes: Figure 48, General Fuselage Skin Repair, of
Subject 53-30-3, Skin Repair, of Chapter 53, Fuselage, of the Boeing 737-100/-200 SRM D6-15565,
Revision 102, dated September 10, 2010.
(2) For Model 737-300 series airplanes: Repair 31, General Fuselage Skin Repairs, of Subject
53-00-01, Fuselage Skin–General, of Chapter 53, Fuselage, of the Boeing 737-300 SRM D6-37635,
Revision 92, dated November 10, 2010.
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(3) For Model 737-400 series airplanes: Repair 31, General Fuselage Skin Repairs, of Subject
53-00-01, Fuselage Skin–General, of Chapter 53, Fuselage, of the Boeing 737-400 SRM D6-38246,
Revision 75, dated November 10, 2010.
(4) For Model 737-500 series airplanes: Repair 31, General Fuselage Skin Repairs, of Subject
53-00-01, Fuselage Skin–General, of Chapter 53, Fuselage, of the Boeing 737-500 SRM D6-38441,
Revision 70, dated November 10, 2010.
(l) Retained Follow-On and Corrective Actions
This paragraph restates the requirements of paragraph (f) of AD 2004-18-06, Amendment 39-
13784 (69 FR 54206, September 8, 2004), with revised service information. If a time-limited repair is
done, as specified in paragraph (j)(1)(i) or (j)(2)(i) of this AD: Do the actions specified in paragraphs
(l)(1), (l)(2), and (l)(3) of this AD, at the times specified in paragraphs (l)(1), (l)(2), and (l)(3) of this
AD, in accordance with the Work Instructions of Boeing Alert Service Bulletin 737-53A1210,
Revision 1, dated October 25, 2001; or in accordance with the Work Instructions of Boeing Alert
Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009.
(1) Within 3,000 flight cycles after doing the repair: Do the actions specified in paragraph
(l)(1)(i) or (l)(1)(ii) of this AD. Then repeat the applicable inspection specified in paragraph (l)(1)(i)
or (l)(1)(ii) of this AD at intervals not to exceed 3,000 flight cycles until permanent rivets are
installed in the repaired area, which ends the repetitive inspections for this paragraph. As of the
effective date of this AD, do only the inspections specified in paragraph (l)(1)(ii) of this AD.
(i) For repairs done before the effective date of this AD: Do a detailed inspection of the repaired
area for loose fasteners in accordance with Part 4 of the Work Instructions of Boeing Alert Service
Bulletin 737-53A1210, Revision 1, dated October 25, 2001, or do the actions specified in paragraph
(l)(1)(ii) of this AD. If any loose fastener is found, before further flight, replace with a new fastener,
in accordance with the Work Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 1,
dated October 25, 2001.
(ii) For repairs done after the effective date of this AD: Do a detailed inspection of the repaired
area for loose, damaged, and missing fasteners, in accordance with Part 6 of the Work Instructions of
Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009. If any loose, missing,
or damaged fastener is found, before further flight, replace with a new fastener, in accordance with
the Work Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16,
2009.
(2) At the applicable time specified in paragraph (l)(2)(i) and (l)(2)(ii) of this AD: Do inspections
of the repaired area for cracking in accordance with Part 4 of the Work Instructions of Boeing Alert
Service Bulletin 737-53A1210, Revision 1, dated October 25, 2001; or in accordance with Part 6 of
the Work Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16,
2009. If any cracking is found, before further flight, repair in accordance with a method approved by
the Manager, Seattle ACO, or in accordance with data meeting the type certification basis of the
airplane if it is approved by the Boeing Commercial Airplanes ODA or any other person authorized
by the Manager, Seattle ACO, to make those findings. For a repair method to be approved the repair
must meet the certification basis of the airplane and the approval must specifically refer to this AD.
(i) For repairs done before the effective date of this AD: Within 4,000 flight cycles after doing
the repair, do the inspections.
(ii) For repairs done on or after the effective date of this AD: Within 3,000 flight cycles after
doing the repair, do the inspections.
(3) At the earlier of the times specified in paragraphs (l)(3)(i) and (l)(3)(ii) of this AD: Make the
repair permanent in accordance with Part 4 and Figure 20 of the Work Instructions of Boeing Alert
Service Bulletin 737-53A1210, Revision 1, dated October 25, 2001, or do the permanent repair, in
accordance with Part 5 of the Work Instructions of Boeing Alert Service Bulletin 737-53A1210,
Revision 3, dated July 16, 2009, which ends the repetitive inspections for the repaired area only. As
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of the effective date of this AD, only Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated
July 16, 2009, may be used to make the repair permanent.
(i) Within 10,000 flight cycles after doing the repair in accordance with Boeing Alert Service
Bulletin 737-53A1210, Revision 1, dated October 25, 2001.
(ii) At the later of the times specified in paragraphs (l)(3)(ii)(A) and (l)(3)(ii)(B) of this AD.
(A) Within 6,000 flight cycles after doing the repair.
(B) Within 1,000 flight cycles after the effective date of this AD.
(m) Retained Optional Terminating Action for Repetitive Eddy Current Inspections
This paragraph restates the requirements of paragraph (g) of AD 2004-18-06, Amendment 39-
13784 (69 FR 54206, September 8, 2004), with revised service information. Accomplishment of
paragraph (b) or (c), as applicable, of AD 2003-14-06, Amendment 39-13225 (68 FR 42956, July 21,
2003), before the effective date of this AD ends the repetitive eddy current inspections required by
paragraph (g) of this AD for that skin panel only; however, the repetitive external detailed inspections
required by paragraph (g) of this AD are still required for all areas. Accomplishing paragraph (b) or
(c), as applicable, of AD 2003-14-06, on or after the effective date of this AD, does not end either the
repetitive detailed or eddy current inspections required by paragraph (g) of this AD.
(n) Retained Credit for Previous Actions
This paragraph restates the provisions of paragraph (h) of AD 2004-18-06, Amendment 39-
13784 (69 FR 54206, September 8, 2004). This paragraph provides credit for actions specified by
paragraphs (g), (h), (i), (j), (k), and (l) of this AD, if those actions were done before October 13, 2004
(the effective date of AD 2004-18-06), using Boeing Alert Service Bulletin 737-53A1210, dated
December 14, 2000 (which is not incorporated by reference in this AD).
(o) Retained Exception to Service Bulletin Procedures
This paragraph restates the provision of paragraph (i) of AD 2004-18-06, Amendment 39-13784
(69 FR 54206, September 8, 2004), with revised service information. For airplanes subject to the
requirements of paragraphs (g) and (h) of this AD: Inspections are not required in areas that are
spanned by an FAA-approved repair that has a minimum of 3 rows of fasteners above and below, or
forward and aft of the chem-milled step, or repairs that have a minimum of 2 rows of fasteners above
and below, or forward and aft of the chem-milled step, and have been installed in accordance with the
requirements of paragraph (k) of this AD. If an external doubler covers the chem-milled step, but
does not span it by a minimum of 3 rows of fasteners above and below, or forward and aft, or does
not have a minimum of 2 rows of fasteners above and below, and have been installed in accordance
with the requirements of paragraph (k) of this AD: In lieu of requesting approval for an alternative
method of compliance (AMOC), one option to comply with the inspection requirement of paragraphs
(g) and (h) of this AD is to inspect all chem-milled steps covered by the repair using the method
specified in the notes in Tables 1 through 6 of paragraph 1.E., ''Compliance,'' and in accordance with
the Work Instructions, of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16,
2009.
(p) For Certain Airplanes: New Repetitive External Detailed and Eddy Current Inspections of
the Crown Area and Other Known Areas of Fuselage Skin Cracking, and Corrective Actions
For Groups 1 through 5 and Groups 9 through 21 airplanes identified in Boeing Alert Service
Bulletin 737-53A1210, Revision 3, dated July 16, 2009, on which the inspections required by
paragraph (g) of this AD have been done before the effective date of this AD: Within 4,500 flight
cycles after doing the most recent inspection required by paragraph (g) of this AD, or within 1,800
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flight cycles after the effective date of this AD, whichever is earlier; do external detailed and eddy
current inspections of the crown area and other known areas of the fuselage skin cracking, in
accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1210, Revision 3, dated July 16, 2009; except as provided by paragraph (o) of this AD. Repeat
the external detailed and eddy current inspections thereafter at intervals not to exceed 1,800 flight
cycles. Accomplishing the inspections required by this paragraph ends the repetitive inspections
required by paragraph (g) of this AD. Before further flight, do all applicable corrective actions as
specified in paragraph (j) of this AD. For the locations specified in Boeing Alert Service Bulletin
737-53A1210, Revision 3, dated July 16, 2009, in lieu of doing detailed inspections, operators may
do general visual inspections, provided that the general visual inspections are done at intervals not to
exceed 1,000 flight cycles.
(q) For Certain Other Airplanes: New Repetitive External Detailed and Eddy Current
Inspections of the Crown Area and Other Known Areas of Fuselage Skin Cracking, and
Corrective Actions
For Groups 1 through 5 and 9 through 21 airplanes identified in Boeing Alert Service Bulletin
737-53A1210, Revision 3, dated July 16, 2009, on which the inspections required by paragraph (g) of
this AD have not been done before the effective date of this AD: Before the accumulation of 28,000
total flight cycles, or within 1,800 flight cycles after the effective date of this AD, whichever is later,
do external detailed and eddy current inspections of the crown area and other known areas of fuselage
skin cracking, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1210, Revision 3, dated July 16, 2009, except as provided by paragraph (o) of this
AD. Repeat the external detailed and eddy current inspections thereafter at intervals not to exceed
1,800 flight cycles. Accomplishing the inspections required by this paragraph ends the repetitive
inspections required by paragraph (g) of this AD. Before further flight, do all applicable corrective
actions as specified in paragraph (j) of this AD. For the locations specified in Boeing Alert Service
Bulletin 737-53A1210, Revision 3, dated July 16, 2009, in lieu of doing detailed inspections,
operators may do general visual inspections, provided that the general visual inspections are done at
intervals not to exceed 1,000 flight cycles.
(r) New Repetitive External Detailed and Eddy Current Inspections of the Fuselage Skin Along
the Chem-Milled Steps of the Butt Joints, and Corrective Actions
For Groups 1 through 5, and 9 through 21 airplanes identified in Boeing Alert Service Bulletin
737-53A1210, Revision 3, dated July 16, 2009: At the later of the times specified in paragraphs (r)(1)
and (r)(2) of this AD, do external detailed and eddy current inspections for vertical cracks in the
fuselage skin along the chem-milled steps of the butt joints, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July
16, 2009, except as provided by paragraph (o) of this AD. Repeat the inspections thereafter at
intervals not to exceed 1,800 flight cycles. If any cracking is found, before further flight, repair in
accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1210, Revision 3, dated July 16, 2009. Doing the repair terminates the repetitive inspections
specified in this paragraph for the repaired area only.
(1) Before the accumulation of 55,000 total flight cycles or 55,000 total flight hours, whichever
occurs first.
(2) Within 1,800 flight cycles after the effective date of this AD.
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(s) New Repetitive Detailed and Eddy Current Inspections Along the Chem-Milled Lines of the
Fuselage Skin of the Lower Lobe Area and Section 41, and Corrective Actions
For Groups 1 through 21 airplanes identified in Boeing Alert Service Bulletin 737-53A1210,
Revision 3, dated July 16, 2009: At the applicable time specified in paragraph (s)(1) or (s)(2) of this
AD, do external detailed and eddy current inspections, as applicable, for horizontal cracks along the
chem-milled lines of the fuselage skin of the lower lobe area and section 41, in accordance with Part
4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3,
dated July 16, 2009, except as provided by paragraphs (o) and (x) of this AD. Repeat the inspections
thereafter at intervals not to exceed 1,800 flight cycles. Accomplishing the inspections required by
this paragraph ends the inspections required by paragraph (h) of this AD. Before further flight, do all
applicable corrective actions as specified in paragraph (j) of this AD. For the locations specified in
Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009, in lieu of doing
detailed inspections, operators may do general visual inspections, provided that the general visual
inspections are done at intervals not to exceed 1,000 flight cycles.
(1) Before the accumulation of 35,000 total flight cycles.
(2) Within 9,000 flight cycles after the most recent inspection required by paragraph (h) of this
AD, or within 1,800 flight cycles after the effective date of this AD, whichever is earlier.
(t) For Certain Airplanes: New Repetitive External Detailed and Eddy Current Inspections
Along the Chem-Milled Lines of the Fuselage Skin of the Window Belt Area, and Corrective
Actions
For Groups 4, 11, and 16 airplanes identified in Boeing Alert Service Bulletin 737-53A1210,
Revision 3, dated July 16, 2009: Before the accumulation of 25,000 total flight cycles or within 1,800
flight cycles after the effective date of this AD, whichever is later, do external detailed and eddy
current inspections for horizontal cracks along the chem-milled lines of the fuselage skin of the
fuselage window belt area, in accordance with Part 2 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009, except as provided by
paragraph (o) of this AD. Repeat the inspections thereafter at intervals not to exceed 1,800 flight
cycles. If any cracking is found, before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (y) of this AD. Doing the repair terminates the repetitive
inspections specified in this paragraph for the repaired area only.
(u) For Certain Other Airplanes: New Repetitive External Detailed and Eddy Current
Inspections Along the Chem-Milled Lines of the Fuselage Skin of the Window Belt Area, and
Corrective Actions
For Groups 3, 5, 9, 10, 12, 14, 15, 17, 18, 19, 20, and 21 airplanes identified in Boeing Alert
Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009: Do the actions specified in
paragraph (u)(1) or (u)(2) of this AD, as applicable. Part 7 (Figure 10) of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009,
specifies applying corrosion inhibiting compound (CIC) Boeing Material Specification (BMS) 3-23
to the surfaces of the repaired area. As an option to using CIC BMS 3-23, operators may use CIC
BMS 3-35, which is equivalent to CIC BMS 3-23.
(1) For airplanes on which the inspections required by paragraph (g) of this AD have been done
before the effective date of this AD: Within 4,500 flight cycles after doing the most recent inspection
required by paragraph (g) of this AD, or within 1,800 flight cycles after the effective date of this AD,
whichever is earlier, do external detailed and eddy current inspections for horizontal cracks along the
chem-milled lines of the fuselage skin of the fuselage window belt area, in accordance with Part 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated
July 16, 2009, except as provided by paragraph (o) of this AD. Repeat the inspections thereafter at
13
intervals not to exceed 1,800 flight cycles. If any cracking is found, before further flight, repair in
accordance with Part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1210, Revision 3, dated July 16, 2009, except as required by paragraph (x) of this AD.
(2) For airplanes on which the inspections required by paragraph (g) of this AD have not been
done before the effective date of this AD: Before the accumulation of 25,000 total flight cycles or
within 1,800 flight cycles after the effective date of this AD, whichever is later, do external detailed
and eddy current inspections for horizontal cracks along the chem-milled lines of the fuselage skin of
the fuselage window belt area, in accordance with Part 2 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009. Repeat the inspections
thereafter at intervals not to exceed 1,800 flight cycles. If any cracking is found, before further flight,
repair in accordance with Part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1210, Revision 3, dated July 16, 2009, except as required by paragraph (x) of this AD.
(v) New Optional Repair
For airplanes on which cracking is found during any inspection required by paragraph (p), (q),
(r), or (s) of this AD, as applicable, doing the repair of the chem-milled area in the skin, as specified
in Part 5 or Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1210, Revision 3, dated July 16, 2009, ends the repetitive external detailed and eddy current
inspections required by paragraph (p), (q), (r), or (s) of this AD, as applicable, for the repaired area
only.
Note 1 to paragraph (v) of this AD: Part 8 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009, specifies a post-repair inspection of
the skin chem-milled crack repair at stringer 12; that inspection is not required by this AD. The
damage tolerance inspections specified in Table 7 of paragraph 1.E., ''Compliance,'' of Boeing Alert
Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009, may be used in support of
compliance with section 121.1109(c)(2) or 129.109(c)(2) of the Code of Federal Regulations (14
CFR 121.1109(c)(2) or 14 CFR 129.109(c)(2)).
(w) New Optional Preventive Modification at Stringer 12
For airplanes on which no cracking is found during any inspection required by paragraph (u) of
this AD, doing the preventive modification of the chem-milled areas in the skin at stringer 12, as
specified in Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1210, Revision 3, dated July 16, 2009, except as required by paragraph (x) of this AD, ends the
repetitive external detailed and eddy current inspections required by paragraph (u) of this AD, for the
modified areas common to stringer 12 only. Part 7 (Figure 10) of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009, specifies applying CIC
BMS 3-23 to the surfaces of the repaired area. As an option to using CIC BMS 3-23, operators may
use CIC BMS 3-35, which is equivalent to CIC BMS 3-23.
(x) Exception to Service Information
Where Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009, specifies to
contact Boeing for repair instructions, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (y) of this AD.
(y) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
14
request to your principal inspector or local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the attention of the person identified in
paragraph (z)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the local flight standards district office/certificate holding district
office.
(3) An AMOC that provides an acceptable level of safety may be used for any repair required by
this AD if it is approved by the Boeing Commercial Airplanes ODA that has been authorized by the
Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 2004-18-06, Amendment 39-13784 (69
FR 54206, September 8, 2004), are approved as AMOCs for the corresponding provisions of this AD.
(5) Inspections and corrective actions required by paragraph (g) of AD 2009-21-01, Amendment
39-16038 (74 FR 52395, October 13, 2009), are approved as AMOCs for the corresponding
provisions of paragraph(s) of this AD, but only for the areas of the lower lobe skin identified in AD
2009-21-01.
(z) Related Information
(1) For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: wayne.lockett@faa.gov.
(2) Service information that is referenced in this AD that is not incorporated by reference in this
AD may be obtained at the addresses identified in paragraphs (aa)(5) and (aa)(6) of this AD.
(aa) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the
service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD,
unless the AD specifies otherwise.
(3) The following service information was approved for IBR on November 6, 2013.
(i) Boeing Alert Service Bulletin 737-53A1210, Revision 3, dated July 16, 2009.
(ii) Figure 48, General Fuselage Skin Repair, of Subject 53-30-3, Skin Repair, of Chapter 53,
Fuselage, of the Boeing 737-100/-200 SRM D6-15565, Revision 102, dated September 10, 2010. The
revision level of this document is identified in only the transmittal letter; no other page of the
document contains this information.
(iii) Repair 31, General Fuselage Skin Repairs, of Subject 53-00-01, Fuselage Skin–General, of
Chapter 53, Fuselage, of the Boeing 737-300 SRM D6-37635, Revision 92, dated November 10,
2010. The revision level of this document is identified in only the transmittal letter; no other page of
the document contains this information.
(iv) Repair 31, General Fuselage Skin Repairs, of Subject 53-00-01, Fuselage Skin–General, of
Chapter 53, Fuselage, of the Boeing 737-400 SRM D6-38246, Revision 75, dated November 10,
2010. The revision level of this document is identified in only the transmittal letter; no other page of
the document contains this information.
(v) Repair 31, General Fuselage Skin Repairs, of Subject 53-00-01, Fuselage Skin–General, of
Chapter 53, Fuselage, of the Boeing 737-500 SRM D6-38441, Revision 70, dated November 10,
2010. The revision level of this document is identified in only the transmittal letter; no other page of
the document contains this information.
(4) The following service information was approved for IBR on October 13, 2004 (69 FR 54206,
September 8, 2004).
15
(i) Boeing Alert Service Bulletin 737-53A1210, Revision 1, excluding Appendix A, dated
October 25, 2001.
(ii) Reserved.
(5) For service information identified in this AD, contact Boeing Commercial Airplanes,
Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(6) You may view this service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call
425-227-1221.
(7) You may view this service information that is incorporated by reference at the National
Archives and Records Administration (NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August 16, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate,
Aircraft Certification Service.
16
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2007-370R1 38144 Braunschweig
EASA AD 2013-0248 vom 14.10.2013 Fax: +49-531-2355-5298
email: ad@LBA.de
AIRBUS 23.10.2013
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: AIRBUS
Hersteller: Airbus, Airbus Industrie
Muster: A300, A300-600, A300-600ST
Baureihen: Alle A300, A310, A300-600 und A300-600ST Baureihen
Werknummern: Alle
Gerätenummer: 2830, EASA.A.014, DGAC TCDS 145
Revisionsstand:
Diese LTA ersetzt D-2007-370 vom 18.12.2007
Airworthiness Directive der ausländischen Behörde:
EASA AD 2013-0248 vom 14.10.2013
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden
sind, wurden durch die EASA über die Entscheidung Nr. 02/2003 übernommen und sind somit ebenfalls
Airworthiness Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2007-370R1 ge-
führt.
Betrifft:
(ATA 05) Time limits / Maintenance checks - Safe life Airworthiness Limitation Items (ALS Part 1) -
Amendment
Anmerkungen:
Gemäß M.A.304 des Anhang I (Teil M) der Verordnung (EG) Nr. 2042/2003 dürfen Luftfahrzeuge
nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in den Betrieb genommen
werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsan-
weisung EASA AD 2013-0248 vom 14.10.2013 herausgegeben oder per Entscheidung Nr. 02/2003
übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsan-
weisungen direkt in der Bundesrepublik Deutschland gültig und bedürfen keiner Umsetzung
durch das Luftfahrt-Bundesamt.
Mit Hilfe dieser Übersichtsseite veröffentlicht das Luftfahrt-Bundesamt ebenfalls die über § 14
Abs. 2 direkt gültige Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und
im Internet unter www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt
keinem Verwaltungsverfahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2007-370R1 Seite 1 von 1 561/2013
