Nachrichten für Luftfahrer 2020 Teil 2 (weicht ggf. von Druckversion ab)
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2020-291 38144 Braunschweig
FAA AD 2020-18-01 - Amdt. 39-21222 Fax: +49-531-2355-5298
email: ad@LBA.de
CESSNA 12.11.2020
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Textron Aviation Inc.
Hersteller: Textron Aviation Inc., vormals Cessna Aircraft Company, Reims Aviation S.A.
Muster: Cessna 172
Cessna 172RG / R172 / 175
Cessna F172
Cessna FR172
Cessna 182
Cessna F182
Cessna 206
Cessna 207
Cessna 210
Baureihen: 172N, 172P, 172Q, 172RG, F172N, F172P, FR172K, R172K, 182E, 182F,
182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, T182, F182P,
F182Q, FR182, R182, TR182, 206, P206, P206A, P206B, P206C, P206D,
P206E, TP206A, TP206B, TP206C, TP206D, TP206E, U206, U206A, U206B,
U206C, U206D, U206E, U206F, U206G, TU206A, TU206B, TU206C, TU206D,
TU206E, TU206F, TU206G, 207, 207A, T207, T207A, 210-5 (205), 210-5A
(205A), 210B, 210C, 210D, 210E, 210F und T210F
Werknummern: 172N Werknummern: 17272885 bis 17274009
172P Werknummern: Alle
172Q Werknummern: 17275869, 17275927 bis 17275934, 17275952,
17275959, 17275960, 17275962, 17275964,
17275965, 17275967, 17275968, 17275969,
17275971, 17275992, 17275999, 17276002,
17276005, 17276029, 17276032, 17276042,
17276045, 17276051, 17276052, 17276054,
17276101, 17276109, 17276140, 17276147,
17276188 und 17276211
172RG Werknummern: Alle
F172N Werknummern: F17201910 bis F17202039
F172P Werknummern: Alle
FR172K Werknummern: FR17200656 bis FR17200675
R172K Werknummern: R1723200 bis R1723454
----------------------------------------------------------------------------------------------------------
182E Werknummern: Alle 182F Werknummern: Alle
182G Werknummern: Alle 182H Werknummern: Alle
182J Werknummern: Alle 182K Werknummern: Alle
182L Werknummern: Alle 182M Werknummern: Alle
182N Werknummern: Alle 182P Werknummern: Alle
182Q Werknummern: Alle 182R Werknummern: Alle
T182 Werknummern: Alle F182P Werknummern: Alle
F182Q Werknummern: Alle FR182 Werknummern: Alle
R182 Werknummern: R18200002 bis R18200583
R182 und TR182 Werknummern: R18200001 und R18200584 bis R18202039
----------------------------------------------------------------------------------------------------------
206 Werknummern: Alle
P206 Werknummern: Alle P206A Werknummern: Alle
P206B Werknummern: Alle P206C Werknummern Alle
P206D Werknummern: Alle P206E Werknummern: Alle
D-2020-291 Seite 1 von 2 496/2020
TP206A Werknummern: Alle TP206B Werknummern: Alle
TP206C Werknummern: Alle TP206D Werknummern: Alle
TP206E Werknummern: Alle
U206 Werknummern: Alle U206A Werknummern: Alle
U206B Werknummern: Alle U206C Werknummern: Alle
U206D Werknummern: Alle U206E Werknummern: Alle
U206F Werknummern: Alle U206G Werknummern: Alle
TU206A Werknummern: Alle TU206B Werknummern: Alle
TU206C Werknummern: Alle TU206D Werknummern: Alle
TU206E Werknummern: Alle TU206F Werknummern: Alle
TU206G Werknummern: Alle
----------------------------------------------------------------------------------------------------------
207 Werknummern: Alle 207A Werknummern: Alle
T207 Werknummern: Alle T207A Werknummern: Alle
----------------------------------------------------------------------------------------------------------
210-5 (205) Werknummern: Alle
210-5A (205A) Werknummern: Alle
210B Werknummern: Alle 210C Werknummern: Alle
210D Werknummern: Alle 210E Werknummern: Alle
210F Werknummern: Alle T210F Werknummern: Alle
----------------------------------------------------------------------------------------------------------
Gerätenummer: 539, 539a, 549, 549a, 549b, 596, 625, 673, 673a, 739, 1003, FAA TCDS 3A12,
FAA TCDS 3A13, FAA TCDS 3A17, FAA TCDS 3A21, FAA TCDS A4CE, FAA
TCDS A4EU, FAA TCDS A16CE, FAA TCDS A18EU, FAA TCDS A42EU
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2020-18-01 - Amdt. 39-21222
Genannte Airworthiness Directives unter dieser Rubrik, die nicht durch die EASA herausgegeben worden sind,
wurden durch die EASA über die Entscheidung Nr. 2019/018/ED übernommen und sind somit ebenfalls Airworthin-
ess Directives der EASA.
Die genannte Airworthiness Directive wird im Luftfahrt-Bundesamt unter der Nummer 2020-291 geführt.
Betrifft:
(ATA 53) Fuselage - Forward Cabin Doorposts at the Strut Attach Fitting - Repetitive Inspections
Anmerkungen:
Gemäß der EU Verordnung Nr. 1321/2014, Anhang I, Teil M, Unterabschnitt C, M.A.301 5.i) und M.A.303 dür-
fen Luftfahrzeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genom-
men werden, wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
FAA AD 2020-18-01 - Amdt. 39-21222 herausgegeben oder per Entscheidung Nr. 2019/018/ED übernommen.
Gemäß § 14 Abs. 2 der Betriebsordnung für Luftfahrtgerät (LuftBO) sind diese Lufttüchtigkeitsanweisun-
gen 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
gültigen Lufttüchtigkeitsanweisungen der EASA in den Nachrichten für Luftfahrer und im Internet unter
www2.LBA.de/LTAs/. Dieser Service dient reinen Informationszwecken und liegt keinem Verwaltungsver-
fahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2020-291 Seite 2 von 2 496/2020
[Federal Register Volume 85, Number 195 (Wednesday, October 7, 2020)]
[Rules and Regulations]
[Pages 63195-63200]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22039]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0049; Product Identifier 2017-CE-031-AD; Amendment 39-21222; AD
2020-18-01]
RIN 2120-AA64
Airworthiness Directives; Textron Aviation Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Textron Aviation
Inc. (Textron) Model 172N, 172P, 172Q, 172RG, F172N, F172P, FR172K, R172K, 182E, 182F,
182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, T182, F182P, F182Q, FR182,
R182, TR182, 206, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C,
TP206D, TP206E, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G, TU206A,
TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, 207, 207A, T207, T207A, 210-5 (205),
210-5A (205A), 210B, 210C, 210D, 210E, 210F, and T210F airplanes. This AD was prompted by
cracks found in the lower area of the forward cabin doorpost bulkhead. This AD requires repetitively
inspecting the lower area of the forward cabin doorposts at the strut attach fitting for cracks and
repairing any cracks. The FAA is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective November 12, 2020.
The Director of the Federal Register approved the incorporation by reference of certain
publications listed in this AD as of November 12, 2020.
ADDRESSES: For service information identified in this final rule, contact Textron Aviation Inc.,
Textron Aviation Customer Service, One Cessna Blvd., Wichita, Kansas 67215; telephone: (316)
517-5800; email: customercare@txtav.com; internet: https://support.cessna.com. You may review
this referenced service information at the FAA, Policy and Innovation Division, 901 Locust, Kansas
City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-
4148. It is also available on the internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0049.
1
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2018-0049; or in person at Docket Operations between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, any
comments received, and other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aerospace Engineer, Wichita
ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4155;
fax: (316) 946-4107; email: bobbie.kroetch@faa.gov or Wichita-COS@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part
39 by adding an AD that would apply to certain serial-numbered Textron Aviation Inc. (Textron)
(type certificate previously held by Cessna Aircraft Company) Model 172N, 172P, 172Q, 172RG,
F172N, F172P, FR172K, R172K, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P,
182Q, 182R, T182, F182P, F182Q, FR182, R182, TR182, 206, P206, P206A, P206B, P206C,
P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, U206, U206A, U206B, U206C,
U206D, U206E, U206F, U206G, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F,
TU206G, 207, 207A, T207, T207A, 210-5 (205), 210-5A (205A), 210B, 210C, 210D, 210E, 210F,
and T210F airplanes. The SNPRM published in the Federal Register on May 29, 2020 (85 FR
32308).
The FAA preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in
the Federal Register on February 1, 2018 (83 FR 4605). The NPRM was prompted by reports of
cracks in the lower area of the forward cabin doorpost bulkhead on more than four dozen Textron 100
and 200 airplanes. The NPRM proposed to require repetitively inspecting the lower area of the
forward cabin doorposts at the strut attach fitting for cracks and repairing any cracks found by
modifying the area with the applicable service kit. The SNPRM proposed to modify the estimated
costs of the proposed AD, the repetitive inspection intervals, and the credit allowed for previous
actions; clarify the inspection instructions for airplanes with the service kit installed; correct the
contact information for obtaining the service information; and add a reporting requirement to collect
the inspection results. The SNPRM also changed some of the model designations listed in the
applicability in order to match the models as they are listed in the type certificate data sheet.
The FAA is issuing this AD to detect and address cracking of the wing strut attach point. The
unsafe condition, if not addressed, could result in failure of the wing in operation, which could result
in loss of control of the airplane.
Comments
The FAA gave the public the opportunity to participate in developing this final rule. The
following presents the comments received on the SNPRM and the FAA's response to each comment.
Support for the SNPRM
Patrick Imperatrice expressed support for the proposed AD.
2
Request To Extend or Remove Calendar Compliance Time
Kermit Bunde expressed support for the 1,000-hour time-in-service (TIS) inspection interval but
requested the FAA remove the 36-month calendar time inspection interval. The commenter stated
that the 36-month interval is too often and that cracking is a function of usage and not only elapsed
time. The commenter provided examples of Cessna maintenance actions that have no calendar time
limit.
The FAA disagrees. Both the manufacturer's guidance, which is published in the supplemental
inspection documents (SIDs) for certain airplanes, and fleet history support the 36-month interval for
inspecting this location. Loading conditions outside of flight, such as ground loads, handling loads,
and tie down loads, may also cause cracking at this location. Therefore, the FAA determined the
inspection interval of 36 calendar months or 1,000 hours TIS, whichever occurs first, is necessary to
address the unsafe condition. The FAA did not change this AD based on this comment.
Conclusion
The FAA reviewed the relevant data, considered the comments received, and determined that air
safety and the public interest require adopting this final rule as proposed.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Cessna Single Engine Service Bulletin SEB93-5, Revision 2, dated May 29,
2019 (SEB93-5R2) and Cessna Single Engine Service Bulletin SEB95-19, dated December 29, 1995
(SEB95-19). For the applicable model airplanes, the service information contains procedures for
repetitively inspecting the lower area of the forward cabin doorposts for cracks and repairing any
cracks found by modifying the area with the applicable Cessna service kit.
This service information is reasonably available because the interested parties have access to it
through their normal course of business or by the means identified in the ADDRESSES section.
Other Related Service Information
The FAA reviewed Cessna Single Engine Service Kit SK172-147, dated December 29, 1995.
This service kit provides instructions to add a channel to each forward cabin doorpost bulkhead. The
FAA also reviewed Cessna Single Engine Service Kit SK182-115, dated December 29, 1995; Cessna
Single Engine Service Kit SK206-42D, dated May 29, 2019; and Cessna Single Engine Service Kit
SK210-156, dated December 29, 1995. For the applicable model airplanes, these service kits provide
instructions to add a doubler and a channel to each forward cabin doorpost bulkhead. In addition, the
FAA reviewed Cessna Single Engine Service Kit SK207-19A, dated May 29, 2019. The service
information contains procedures to reinforce the lower forward doorpost bulkhead and wing strut
fitting by adding a doubler and a channel to each forward cabin doorpost bulkhead.
Costs of Compliance
The FAA estimates that this AD affects 14,653 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
3
Estimated Costs
Action Labor cost Parts cost Cost per Cost on U.S.
product operators
Inspect the lower area of the 1.5 work-hours × Not $127.50 $1,868,257.50
forward cabin doorposts for $85 per hour = applicable
cracks $127.50
Reporting requirement 1 work-hour × $85 Not $85 $1,245,505
per hour = $85 applicable
The FAA estimates the following costs to do any necessary repairs that would be required based
on the results of the inspection. Reference the applicable Cessna single engine service bulletin for kit
applicability. The FAA has no way of determining the number of airplanes that might need this
repair.
On-Condition Costs
Action Labor cost Parts Cost per
cost product
Install Cessna Single-Engine Service Kit 36 work-hours × $85 per hour $3,415 $6,475
SK172-147 = $3,060
Install Cessna Single-Engine Service Kit 36 work-hours × $85 per hour $7,490 $10,550
SK182-115 = $3,060
Install Cessna Single-Engine Service Kit 36 work-hours × $85 per hour $3,115 $6,175
SK206-42D = $3,060
Install Cessna Single-Engine Service Kit 36 work-hours × $85 per hour $4,957 $8,017
SK207-19A = $3,060
Install Cessna Single-Engine Service Kit 36 work-hours × $85 per hour $7,020 $10,080
SK210-156 = $3,060
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor
shall a person be subject to penalty for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that collection of information displays a
current valid OMB control number. The control number for the collection of information required by
this AD is 2120-0056. Public reporting for this collection of information is estimated to be
approximately 1 hour per response, including the time for reviewing instructions, searching existing
data sources, gathering and maintaining the data needed, completing and reviewing the collection of
information. All responses to this collection of information are mandatory. Send comments regarding
this burden estimate or any other aspect of this collection of information, including suggestions for
reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration,
10101 Hillwood Parkway, Fort Worth, TX 76177-1524.
4
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation
Programs, describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart
III, Section 44701: General requirements. Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order 13132. This AD will not
have a substantial direct effect on the States, on the relationship between the national government and
the States, or on the distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that this AD:
(1) Is not a “significant regulatory action” under Executive Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of
small entities under the criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR
part 39 as follows:
PART 39–AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
5
AIRWORTHINESS
FAA DIRECTIVE
Aviation Safety
www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html
2020-18-01 Textron Aviation Inc.: Amendment 39-21222; Docket No. FAA 2018-0049; Product
Identifier 2017-CE-031-AD.
(a) Effective Date
This AD is effective November 12, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Textron Aviation Inc. (type certificate previously held by
Cessna Aircraft Company) model airplanes, certificated in any category:
6
7
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code
53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of cracks found in the lower area of the forward cabin
doorpost bulkhead. The FAA is issuing this AD to detect and address cracking of the wing strut
attach point. The unsafe condition, if not addressed, could result in failure of the wing in operation,
which could result in loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Initial Inspections
(1) For airplanes without a lower forward doorpost bulkhead and wing strut fitting reinforcement
service kit (service kit) installed in accordance with Cessna Single Engine Service Bulletin SEB95-
19, dated December 29, 1995 (SEB95-19), or Cessna Single Engine Service Bulletin SEB93-5,
Revision 2, dated May 29, 2019 (SEB93-5R2): At the applicable compliance time specified in
paragraph (g)(1)(i) or (ii) of this AD, do a visual inspection of the lower forward doorpost at the strut
attach fitting for cracks in accordance with steps 1.A., 1.B., 1.C., and 1.B. (the step following step
1.C.) of the Accomplishment Instructions in SEB95-19; or steps 1.A. and 1.B. of the
Accomplishment Instructions in SEB93-5R2; as applicable to your model airplane.
(i) For airplanes that have accumulated less than 4,000 hours time-in-service (TIS) as of the
effective date of this AD: Initially inspect prior to the accumulation of 4,000 hours TIS or within the
next 200 hours TIS after the effective date of this AD, whichever occurs later.
(ii) For airplanes that have accumulated 4,000 or more hours TIS as of the effective date of this
AD: Initially inspect within 200 hours TIS after the effective date of this AD or within 12 calendar
months after the effective date of this AD, whichever occurs first.
8
