Nachrichten für Luftfahrer 2016 Teil 2 (weicht ggf. von Druckversion ab)
Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Katheryn Malatek, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA
01803; phone: 781-238-7747; fax: 781-238-7199; email: katheryn.malatek@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD
that would apply to certain PW PW4000-94 inch turbofan engines with HPC 10th stage disk, part
number (P/N) 51H710 or 53H976-06, installed and certain PW4000-100 inch turbofan engines with
HPC 10th stage disk, P/N 53H976-06, installed. The NPRM published in the Federal Register on
December 9, 2015 (80 FR 76400). The NPRM was prompted by a report of a crack found in the HPC
10th stage disk. The root cause of the crack was a manual polishing procedure, previously used
during manufacture, that caused surface scratches on the disk. The NPRM proposed to require a USI
or ECI of the HPC 10th stage disk. We are issuing this AD to prevent failure of the HPC 10th stage
disk, which could lead to an uncontained disk release, damage to the engine, and damage to the
airplane.
Comments
We gave the public the opportunity to participate in developing this AD. The following presents
the comments received on the NPRM (80 FR 76400, December 9, 2015) and the FAA's response to
each comment.
Support for the NPRM
The Boeing Company and United Airlines expressed support for the NPRM (80 FR 76400,
December 9, 2015).
Request To Use ECI as Follow-on to USI
American Airlines requested that we revise Compliance paragraph (e) of this AD to add a
statement that the ECI can be used to confirm the presence of a crack if a USI is initially performed
and the ECI is the final authority on whether or not a crack is present on the disk.
We agree. We revised Compliance paragraph (e) of this AD to allow a follow-on ECI.
Request To Allow Disk Replacement Repairs
Atlas Air requested that we revise the Compliance paragraph (e) of this AD to allow use of disk
replacement repairs per the PW PW4000-94/100 Clean, Inspect, Repair (CIR) Manual Part No.
51A357, Section 72-35-10, Repair 07.
We disagree. This AD requires removal of the 10th stage disk if it fails inspection. There are no
FAA-approved repairs allowed on the 10th stage disk. The previously approved PW4000-94/100 CIR
Manual Part No. 51A357, Section 72-35-07, Repair 04 to the drum rotor, replaces the disk, resulting
in a part eligible for installation. We did not change this AD.
2
Request To Allow ECI at Overhaul
Air India Limited requested that Compliance paragraph (e) of this AD allow an ECI when the
HPC is ''overhauled'' rather than when it is ''removed from the engine.'' Air India Limited indicated
that ''overhauled'' is clearer than ''removed from the engine''.
We disagree. The intent of this AD is to inspect the 10th stage disk at exposure. The phrase,
''Whenever the HPC front drum rotor is removed from the engine . . .'' clearly describes the
appropriate level of exposure for performing the ECI. We did not change this AD.
Request To Waive Repeat USI
Air India Limited requested that we revise Compliance paragraph (e) of this AD to indicate that a
repeat USI should be waived to reduce the maintenance burden if the low-pressure turbine (LPT) is
removed in less than 100 hours since the last USI.
We disagree. Our safety risk assessment assumed that a USI is performed whenever the high-
pressure turbine (HPT) or LPT is removed from the engine and an ECI is performed whenever the
HPC front drum rotor disk assembly is removed from the engine. We determined the inspection
interval in the Compliance paragraph (e) of this AD provides an acceptable level of safety. We did
not change this AD.
Request To Remove Compliance Statement
FedEx requested that we revise Compliance paragraph (e) of this AD to remove the statement,
''Comply with this AD within the compliance times specified, unless already done.'' FedEx stated that
there are no compliance times specified and the compliance requires a repetitive inspection, so the
statement does not apply.
We disagree. The statement ''. . . unless already done'' allows an operator who has performed an
initial inspection before the effective date of the AD, but has not yet returned the part to service, to
take credit for that action. While there is no calendar or cyclic time given, the requirements of this
AD must be met when the HPT, LPT, or HPC front drum rotor disk assembly is removed from the
engine. We did not change this AD.
Conclusion
We reviewed the relevant data, considered the comments received, and determined that air safety
and the public interest require adopting this AD with the changes described previously. We have
determined that these minor changes:
• Are consistent with the intent that was proposed in the NPRM (80 FR 76400, December 9,
2015) for correcting the unsafe condition; and
• Do not add any additional burden upon the public than was already proposed in the NPRM
(80 FR 76400, December 9, 2015).
We also determined that these changes will not increase the economic burden on any operator or
increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed PW Alert Service Bulletin (ASB) PW4G-100-A72-255, dated August 31, 2015 and
PW ASB PW4ENG A72-833, dated August 20, 2015. The ASBs provide lists of affected HPC disks
and describe procedures for USI and ECI of the HPC 10th stage disk. 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.
3
Costs of Compliance
We estimate that this AD affects 763 engines installed on airplanes of U.S. registry. We also
estimate that it would take about 12 hours per engine to do the inspection. The average labor rate is
$85 per hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be
$778,260.
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.
We are 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) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979),
(3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory
distinction, and
(4) 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):
4
AIRWORTHINESS DIRECTIVE
FAA
www.faa.gov/aircraft/safety/alerts/
Aviation Safety
www.gpoaccess.gov/fr/advanced.html
2016-08-09 Pratt & Whitney Division: Amendment 39-18485; FAA-2015-4474; Directorate
Identifier 2015-NE-34-AD.
(a) Effective Date
This AD is effective June 1, 2016.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all Pratt & Whitney Division (PW) PW4050, PW4052, PW4056,
PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4152, PW4156, PW4156A, PW4158,
PW4160, PW4460, PW4462, and PW4650 turbofan engines, including models with a ''-3'' suffix,
with one of the following installed:
(i) High-pressure compressor (HPC) 10th stage disk, part number (P/N) 51H710, with a serial
number (S/N) listed in Table 1 of PW Alert Service Bulletin (ASB) PW4ENG A72-833, dated
August 20, 2015; or
(ii) HPC 10th stage disk, P/N 53H976-06, with an S/N listed in Table 2 of PW ASB PW4ENG
A72-833, dated August 20, 2015.
(2) This AD also applies to all PW PW4164, PW4168, PW4168A, PW4164C, PW4164C/B,
PW4170, PW4168A-1D, PW4168-1D, PW4164-1D, PW4164C-1D, and PW4164C/B-1D turbofan
engines with an HPC 10th stage disk, P/N 53H976-06, with an S/N listed Table 1 of PW ASB
PW4G-100-A72-255, dated August 31, 2015, installed.
(d) Unsafe Condition
This AD was prompted by a report of a crack found in the HPC 10th stage disk. We are issuing
this AD to prevent failure of the HPC 10th stage disk, uncontained disk release, damage to the
engine, and damage to the airplane.
(e) Compliance
Comply with this AD within the compliance times specified, unless already done.
(1) After the effective date of this AD, whenever the high-pressure turbine (HPT) or low-
pressure turbine (LPT) is removed from the engine, perform an ultrasonic inspection (USI) of the
HPC 10th stage disk for cracks. If the HPC 10th stage disk fails the USI, perform a follow-on eddy
current inspection (ECI) or remove the disk from service and replace with a part eligible for
installation.
(2) After the effective date of this AD, whenever the HPC front drum rotor disk assembly is
removed from the engine, perform an ECI of the HPC 10th stage disk for cracks. Remove from
service any HPC 10th stage disk that fails inspection and replace with a part eligible for installation.
A USI as required by paragraph (e)(1) of this AD is not required if an ECI is performed.
5
(f) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the
procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-
AMOC@faa.gov.
(g) Related Information
For more information about this AD, contact Katheryn Malatek, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA
01803; phone: 781-238-7747; fax: 781-238-7199; email: katheryn.malatek@faa.gov.
(h) 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.
(i) Pratt & Whitney (PW) Alert Service Bulletin (ASB) PW4G-100-A72-255, dated August 31,
2015.
(ii) PW ASB PW4ENG A72-833, dated August 20, 2015.
(3) For PW service information identified in this AD, contact Pratt & Whitney Division, 400
Main St., East Hartford, CT 06108; phone: 860-565-8770; fax: 860-565-4503.
(4) You may view this service information at FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call
781-238-7125.
(5) 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 Burlington, Massachusetts, on April 7, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
6
Lufttüchtigkeitsanweisung Luftfahrt-Bundesamt
- Sachgebiet T23 -
D-2016-141 38144 Braunschweig
FAA AD 2016-08-18 - Amdt. 39-18495 Fax: +49-531-2355-5298
email: ad@LBA.de
PIPER 31.05.2016
Betroffenes Luftfahrtgerät:
Art des Luftfahrtgerätes: Flugzeug
Inhaber der Musterzulassung: Piper Aircraft, Inc.
Hersteller: Piper Aircraft, Inc.
Muster: Piper PA-31
Baureihen: PA-31-350
Werknummern: 31-5001 bis 31-5004, 31-7305005 bis 31-8452024, 31-8253001 bis 31-
8553002.
Betroffen sind alle PA-31-350 Flugzeuge der genannten Werknummern mit
Lycoming Triebwerken TIO-540-J2B, LTIO-540-J2B, TIO-540-J2BD und LTIO-
540-J2BD, die mit folgenden Kraftstoffleitungen ausgerüstet sind: - Piper
Teilenummer (P/N) 39995-034 (inlet fuel hose to engine fuel pump) - Lycoming
Teilenummer (P/N) LW-12877-6S142 (exit fuel hose from engine fuel pump)
Gerätenummer: 2039, FAA TCDS A20SO
Revisionsstand:
Originalausgabe
Airworthiness Directive der ausländischen Behörde:
FAA AD 2016-08-18 - Amdt. 39-18495
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 2016-141 geführt.
Betrifft:
(ATA 73) Engine Fuel and Control - Fuel hose Assembly / Turbocharger Support Assembly - Inspection
Anmerkungen:
Gemäß M.A.303 und M.A.301 5.i) des Anhang I der Verordnung (EU) Nr. 1321/2014 (Teil-M) dürfen Luftfahr-
zeuge nach dem in der Lufttüchtigkeitsanweisung angegebenen Termin nur in Betrieb genommen werden,
wenn die angeordneten Maßnahmen ordnungsgemäß durchgeführt worden sind.
Die Europäische Agentur für Flugsicherheit (EASA) hat die oben referenzierte Lufttüchtigkeitsanweisung
FAA AD 2016-08-18 - Amdt. 39-18495 herausgegeben oder per Entscheidung Nr. 02/2003 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
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 Verwaltungsver-
fahren zu Grunde. Rechtsmittel sind damit ausgeschlossen.
D-2016-141 Seite 1 von 1 225/2016
[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)]
[Rules and Regulations]
[Pages 26106-26109]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-09238]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0338; Directorate Identifier 2014-CE-010-AD; Amendment 39-18495;
AD 2016-08-18]
RIN 2120-AA64
Airworthiness Directives; Piper Aircraft, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc.
Model PA-31-350 airplanes. This AD was prompted by a report of an engine fire caused by a leak in
the fuel pump inlet hose. This AD requires inspecting the fuel hose assembly and the turbocharger
support assembly for proper clearance between them, inspecting each assembly for any sign of
damage, and making any necessary repairs or replacements. We are issuing this AD to correct the
unsafe condition on these products.
DATES: This AD is effective June 6, 2016.
The Director of the Federal Register approved the incorporation by reference of a certain
publication listed in this AD as of June 6, 2016.
ADDRESSES: For service information identified in this final rule, contact Piper Aircraft, Inc., 2926
Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567-4361; fax: (772) 978-6573; Internet:
www.piper.com/home/pages/Publications.cfm. You may view this referenced service information at
the FAA, Small Airplane Directorate, 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
http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0338.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2014-0338; or in person at the Docket Management Facility between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD,
the regulatory evaluation, any comments received, and other information. The address for the Docket
Office (phone: 800-647-5527) is Document Management Facility, U.S. Department of
1
Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary Wechsler, Aerospace Engineer, FAA,
Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, Georgia 30337;
telephone: (404) 474-5575; fax: (404) 474-5606; email: gary.wechsler@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by
adding an AD that would apply to certain Piper Aircraft, Inc. Model PA-31-350 airplanes. The
SNPRM published in the Federal Register on January 26, 2016 (81 FR 4214). We preceded the
SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on
June 3, 2014 (79 FR 31888). The NPRM proposed to require inspecting the fuel hose assembly and
the turbocharger support assembly for proper clearance between them, inspecting each assembly for
any sign of damage, and making any necessary repairs or replacements. The NPRM was prompted by
a report of an engine fire on a Piper Aircraft, Inc. (Piper) Model PA-31-350 airplane. Investigation
revealed that the fire was caused by a leak in the fuel pump inlet hose that resulted from repeated
contact with an adjacent turbocharger support assembly caused by inadequate clearance between the
two assemblies. The SNPRM proposed to require the same actions as proposed in the NPRM using
revised service information issued by the manufacturer to clarify which engines are part of the
airplane applicability and to revise the instructions for accomplishing the proposed actions.
This condition, if not corrected, could result in damage to the fuel inlet hose assembly, which
could cause the fuel pump inlet hose to fail and leak fuel in the engine compartment. This condition
could also cause damage to the turbocharger support assembly, which could require the turbocharger
support assembly to be repaired or replaced.
Comments
We gave the public the opportunity to participate in developing this AD. We received no
comments on the SNPRM (81 FR 4214, January 26, 2016) or on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and determined that air safety and the public interest require
adopting this AD as proposed except for minor editorial changes. We have determined that these
minor changes:
• Are consistent with the intent that was proposed in the SNPRM (81 FR 4214, January 26,
2016) for correcting the unsafe condition; and
• Do not add any additional burden upon the public than was already proposed in the SNPRM
(81 FR 4214, January 26, 2016).
Related Service Information Under 1 CFR Part 51
We reviewed Piper Aircraft, Inc. Service Bulletin No. 1257A, dated August 4, 2015. The service
information describes procedures for the following. 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.
2
–Inspecting for a minimum 3/16-inch clearance between the fuel hose assembly and the turbocharger
support assembly and making any necessary adjustments.
–Inspecting the fuel hose assembly for any signs of damage and, if necessary, replacing with a
serviceable part.
–Inspecting the turbocharger support assembly for any signs of damage and, if necessary, repairing or
replacing with a serviceable part.
–Performing an engine run-up to check for any leaks.
Differences Between This AD and the Service Information
There are differences between the compliance times for the corrective actions in this AD and
those in the related service information.
We based the compliance times in this AD on risk analysis and cost impact to operators. There
has only been one event of the reported incident in the operational history of Piper Model PA-31-350
airplanes. Cost was also a strong consideration due to the age of the fleet and the number of airplanes
still in service.
The one-time inspection required in this AD is very inexpensive and requires minimal time to
accomplish. It is expected that almost all airplanes in service can be cleared with a single inspection,
and no additional actions or costs would be incurred by the vast majority of the fleet.
We determined that a single inspection with any necessary corrective actions is an adequate
terminating action for the unsafe condition. The risk related to future maintenance on the fuel line
would be mitigated by the related service information and awareness from this AD.
Costs of Compliance
We estimate that this AD affects 773 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
Action Labor cost Parts Cost per Cost on U.S.
cost product operators
Inspect for proper clearance between the .5 work-hour × $85 N/A $42.50 $32,852.50
fuel hose assembly and the turbocharger per hour = $85
support assembly
Inspect the fuel hose assembly for .5 work-hour × $85 N/A 42.50 32,852.50
evidence of leaking, cracking, chafing, per hour = $42.50
and any other sign of damage
Inspect the turbocharger support assembly .5 work-hour × $85 N/A 42.50 32,852.50
for evidence of chafing and any other sign per hour = $42.50
of damage
Engine run-up/leak check 1 work-hour × $85 = N/A 85 65,705
$85 (.5 work hour
per engine)
We estimate the following costs to do any necessary follow-on actions that will be required
based on the results of the inspection. We have no way of determining the number of airplanes that
might need these corrective actions.
3
On-Condition Costs
Action Labor cost Parts Cost per
cost product
Adjust routing of fuel hose assembly for proper clearance 5.5 work-hours × N/A $467.50
between the fuel hose assembly and the turbocharger $85 per hour =
support assembly $467.50
Replace Piper fuel pump inlet hose assembly, part 1 work-hour × $85 1,068 1,153
number 39995-34 (2 per airplane) per hour = $85
Replace Lycoming turbocharger support assembly, part 24 work-hours × 12,874 14,914
number LW-18302 (2 per airplane) $85 per hour =
$2,040
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.
We are 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) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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:
4
