81 FR 24696 - Airworthiness Directives; Pratt & Whitney Division Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 81 (April 27, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 81 (April 27, 2016)
| Page Range | 24696-24699 | |
| FR Document | 2016-09687 |
[Federal Register Volume 81, Number 81 (Wednesday, April 27, 2016)] [Rules and Regulations] [Pages 24696-24699] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-09687] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4474; Directorate Identifier 2015-NE-34-AD; Amendment 39-18485; AD 2016-08-09] RIN 2120-AA64 Airworthiness Directives; Pratt & Whitney Division Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain [[Page 24697]] Pratt & Whitney Division (PW) PW4000-94 inch and PW4000-100 inch model turbofan engines. This AD was prompted by a report of a crack found in the high-pressure compressor (HPC) 10th stage disk. This AD requires performing an ultrasonic inspection (USI) or an eddy current inspection (ECI) of 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. DATES: This AD is effective June 1, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 1, 2016. ADDRESSES: For service information identified in this final rule, contact Pratt & Whitney Division, 400 Main St., East Hartford, CT 06108; phone: 860 565-8770; fax: 860 565-4503. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call (781) 238-7125. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-4474. 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-2015- 4474; 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 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: [email protected]. 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. 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:[Agr]re 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 [[Page 24698]] 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. 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 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 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. (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: [email protected]. (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: [email protected]. (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 [[Page 24699]] 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. [FR Doc. 2016-09687 Filed 4-26-16; 8:45 am] BILLING CODE 4910-13-P
![24696 Federal Register / Vol. 81, No. 81 / Wednesday, April 27, 2016 / Rules and Regulations
the SB specifically list the fleets FAA promulgates ADs with specific require an operator who cannot comply
affected, and which steps are applicable standards to directly address the with the specific requirements of an AD
based on several different configurations identified unsafe condition. As to request FAA approval of an AMOC.
of various aircraft. Therefore, the exemplified by AD 2007–07–02, ADs The operator must obtain an AMOC
commenter concluded there is no need often require many different actions for approval even if the affected product
to include the word ‘‘applicable’’ to various models and aircraft has been removed from the aircraft,
exclude those products for which the configurations. Because of those rendering compliance with the specific
requirements clearly do not apply. complexities, mandating AD actions requirements of the AD impossible. The
ARSA commented that under part 39 without incorporating by reference the AMOC process allows the FAA to
the FAA cannot make anything manufacturer’s service bulletin that may determine whether the unsafe condition
‘‘applicable’’ that is not directly related contain ‘‘normal’’ part 43 maintenance has been eliminated when an operator
to the unsafe condition and specified actions becomes impracticable or may removes a component to which an AD
actions must be limited to those that interject unnecessary complexities or applies and replaces it with a different
directly address the unsafe condition. In inconsistencies that adversely affect component.
its view, the FAA’s interpretation performance of the necessary corrective This approach was clearly specified
mandates accomplishing all actions, actions. in the FAA’s part 39 rulemaking in
whether or not necessary to correcting 2002. See Airworthiness Directives, 67
the unsafe condition, which is contrary Question 4: What is the extent of an
aircraft operator’s responsibilities when FR 47998 (‘‘Specifically, FAA is adding
to part 39. to part 39 the language explaining that
an AD requires an action that cannot be
FAA’s Response to Comments accomplished on a particular aircraft? ADs apply even if products have been
modified, altered, or repaired in the area
The FAA intends ‘‘applicable’’ to Answer: Sections 39.15 and 39.17 addressed by the directive.’’). The 2002
have the same meaning in both places require ADs to apply to a specific rulemaking did not introduce any new
in paragraph (f) of AD 2007–07–02. The product, even if the product has been regulatory requirements; rather, the
first usage limits the required actions to changed through component removal or FAA simply codified in part 39
those that apply to a particular aircraft replacement or other modification. An provisions currently found in ADs. Id. at
under the specific conditions found; it operator who cannot comply with the 47999. If a change in a product affects
does not permit an operator to decide specific requirements of an AD must one’s ability to comply with the AD, the
which actions are necessary and which request approval of an AMOC from the person operating the aircraft or using
are unnecessary to correct the unsafe FAA. The operator must obtain an the product must ask the FAA’s
condition. AMOC approval even if the affected
The second usage references Table 1 permission to use an AMOC, and the
component has been removed from the request must either show that the
in the AD that identifies the model of aircraft, rendering compliance with the
aircraft to which each service bulletin change eliminated the unsafe condition
specific requirements of the AD or include the specific actions proposed.
applies. The ‘‘applicable service impossible. The AMOC process allows
bulletin’’ means the service bulletin that Id. at 48000.
the FAA to determine whether the This response was coordinated with
applies to each corresponding aircraft unsafe condition has been eliminated
model, as indicated in Table 1 of the the Aircraft Maintenance Division of the
when an operator removes a component Flight Standards Service and the Design,
AD. Similarly, ‘‘all the applicable addressed in an AD and replaces it with
actions’’ specified in each applicable Manufacturing and Airworthiness
a different component. Division of the Aircraft Certification
service bulletin are those actions that
are identified as applying to a particular Summary of Comments Service.
aircraft. ‘‘Applicable’’ is a necessary Some commenters stated the FAA’s Issued in Washington, DC, on April 19,
qualifier in this context for two reasons: interpretation is either wrong because 2016.
(1) In many ADs, the referenced service when the AD pertains to a specific part Lorelei Peter,
bulletins specify different actions for or component that has since been Assistant Chief Counsel for Regulations.
different aircraft configurations, legally removed or pertains to a part or [FR Doc. 2016–09667 Filed 4–26–16; 8:45 am]
typically identified as ‘‘Group 1,’’ such that is not installed on the aircraft, BILLING CODE 4910–13–P
‘‘Group 2,’’ etc.; (2) in many ADs, the the AD no longer applies, or represents
referenced service bulletins specify a change from past practice or guidance.
different actions depending on DEPARTMENT OF TRANSPORTATION
conditions found during performance of FAA Response to Comments
previous steps in the instructions (e.g., If a change to a product makes it Federal Aviation Administration
if a crack is smaller than a specified impossible to comply with the
size, repair in accordance with the requirements of an AD, then the 14 CFR Part 39
Structural Repair Manual; if larger, operator must request an AMOC
[Docket No. FAA–2015–4474; Directorate
repair in accordance with a method approval from the FAA. Sections 39.15 Identifier 2015–NE–34–AD; Amendment 39–
approved by the Aircraft Certification and 39.17 directly answer this issue. 18485; AD 2016–08–09]
Office). The term ‘‘applicable’’ limits the Section 39.15 provides that an AD
AD’s requirements to only those that are applies to each product identified in the RIN 2120–AA64
specified in the service bulletin for the AD, even if an individual product has
Airworthiness Directives; Pratt &
configuration and conditions of a been changed by modifying, altering, or
Whitney Division Turbofan Engines
jstallworth on DSK7TPTVN1PROD with RULES
particular aircraft. In this case, the word repairing it in the area addressed by the
‘‘all’’ means that every applicable action AD. Section 39.17 requires that if a AGENCY: Federal Aviation
must be accomplished. change in a product affects an operator’s Administration (FAA), DOT.
Although this response applies ability to accomplish the actions ACTION: Final rule.
specifically to AD 2007–07–02, this required by the AD in any way, the
general principle also applies to uses of operator must request FAA approval of SUMMARY: We are adopting a new
the term ‘‘applicable’’ in other ADs. The an AMOC. Together these sections airworthiness directive (AD) for certain
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proposed in the NPRM (80 FR 76400, (1) Is not a ‘‘significant regulatory (d) Unsafe Condition
December 9, 2015). action’’ under Executive Order 12866, This AD was prompted by a report of a
We also determined that these (2) Is not a ‘‘significant rule’’ under crack found in the HPC 10th stage disk. We
changes will not increase the economic DOT Regulatory Policies and Procedures are issuing this AD to prevent failure of the
burden on any operator or increase the (44 FR 11034, February 26, 1979), HPC 10th stage disk, uncontained disk
scope of this AD. release, damage to the engine, and damage to
(3) Will not affect intrastate aviation the airplane.
Related Service Information Under 1 in Alaska to the extent that it justifies
making a regulatory distinction, and (e) Compliance
CFR Part 51
(4) Will not have a significant Comply with this AD within the
We reviewed PW Alert Service compliance times specified, unless already
Bulletin (ASB) PW4G–100–A72–255, economic impact, positive or negative,
done.
dated August 31, 2015 and PW ASB on a substantial number of small entities (1) After the effective date of this AD,
PW4ENG A72–833, dated August 20, under the criteria of the Regulatory whenever the high-pressure turbine (HPT) or
2015. The ASBs provide lists of affected Flexibility Act. low-pressure turbine (LPT) is removed from
HPC disks and describe procedures for List of Subjects in 14 CFR Part 39 the engine, perform an ultrasonic inspection
USI and ECI of the HPC 10th stage disk. (USI) of the HPC 10th stage disk for cracks.
Air transportation, Aircraft, Aviation If the HPC 10th stage disk fails the USI,
This service information is reasonably perform a follow-on eddy current inspection
available because the interested parties safety, Incorporation by reference,
Safety. (ECI) or remove the disk from service and
have access to it through their normal replace with a part eligible for installation.
course of business or by the means Adoption of the Amendment (2) After the effective date of this AD,
identified in the ADDRESSES section. whenever the HPC front drum rotor disk
Accordingly, under the authority assembly is removed from the engine,
Costs of Compliance delegated to me by the Administrator, perform an ECI of the HPC 10th stage disk
We estimate that this AD affects 763 the FAA amends 14 CFR part 39 as for cracks. Remove from service any HPC
engines installed on airplanes of U.S. follows: 10th stage disk that fails inspection and
registry. We also estimate that it would replace with a part eligible for installation. A
PART 39—AIRWORTHINESS USI as required by paragraph (e)(1) of this AD
take about 12 hours per engine to do the
DIRECTIVES is not required if an ECI is performed.
inspection. The average labor rate is $85
per hour. Based on these figures, we (f) Alternative Methods of Compliance
estimate the cost of this AD on U.S. ■ 1. The authority citation for part 39 (AMOCs)
operators to be $778,260. continues to read as follows: The Manager, Engine Certification Office,
Authority: 49 U.S.C. 106(g), 40113, 44701. FAA, may approve AMOCs for this AD. Use
Authority for This Rulemaking the procedures found in 14 CFR 39.19 to
Title 49 of the United States Code § 39.13 [Amended] make your request. You may email your
specifies the FAA’s authority to issue request to: ANE–AD–AMOC@faa.gov.
■ 2. The FAA amends § 39.13 by adding
rules on aviation safety. Subtitle I, the following new airworthiness (g) Related Information
section 106, describes the authority of directive (AD): For more information about this AD,
the FAA Administrator. Subtitle VII: 2016–08–09 Pratt & Whitney Division: contact Katheryn Malatek, Aerospace
Aviation Programs, describes in more Amendment 39–18485; FAA–2015–4474; Engineer, Engine Certification Office, FAA,
detail the scope of the Agency’s Directorate Identifier 2015–NE–34–AD. Engine & Propeller Directorate, 1200 District
authority. Avenue, Burlington, MA 01803; phone: 781–
We are issuing this rulemaking under (a) Effective Date 238–7747; fax: 781–238–7199; email:
the authority described in Subtitle VII, This AD is effective June 1, 2016. katheryn.malatek@faa.gov.
Part A, Subpart III, Section 44701: (b) Affected ADs (h) Material Incorporated by Reference
‘‘General requirements.’’ Under that (1) The Director of the Federal Register
None.
section, Congress charges the FAA with approved the incorporation by reference
promoting safe flight of civil aircraft in (c) Applicability (IBR) of the service information listed in this
air commerce by prescribing regulations (1) This AD applies to all Pratt & Whitney paragraph under 5 U.S.C. 552(a) and 1 CFR
for practices, methods, and procedures Division (PW) PW4050, PW4052, PW4056, part 51.
the Administrator finds necessary for PW4060, PW4060A, PW4060C, PW4062, (2) You must use this service information
safety in air commerce. This regulation PW4062A, PW4152, PW4156, PW4156A, as applicable to do the actions required by
is within the scope of that authority PW4158, PW4160, PW4460, PW4462, and this AD, unless the AD specifies otherwise.
PW4650 turbofan engines, including models (i) Pratt & Whitney (PW) Alert Service
because it addresses an unsafe condition
with a ‘‘-3’’ suffix, with one of the following Bulletin (ASB) PW4G–100–A72–255, dated
that is likely to exist or develop on installed: August 31, 2015.
products identified in this rulemaking (i) High-pressure compressor (HPC) 10th (ii) PW ASB PW4ENG A72–833, dated
action. stage disk, part number (P/N) 51H710, with August 20, 2015.
a serial number (S/N) listed in Table 1 of PW (3) For PW service information identified
Regulatory Findings
Alert Service Bulletin (ASB) PW4ENG A72– in this AD, contact Pratt & Whitney Division,
This AD will not have federalism 833, dated August 20, 2015; or 400 Main St., East Hartford, CT 06108;
implications under Executive Order (ii) HPC 10th stage disk, P/N 53H976–06, phone: 860–565–8770; fax: 860–565–4503.
13132. This AD will not have a with an S/N listed in Table 2 of PW ASB (4) You may view this service information
substantial direct effect on the States, on PW4ENG A72–833, dated August 20, 2015. at FAA, Engine & Propeller Directorate, 1200
jstallworth on DSK7TPTVN1PROD with RULES
the relationship between the national (2) This AD also applies to all PW PW4164, District Avenue, Burlington, MA. For
PW4168, PW4168A, PW4164C, PW4164C/B, information on the availability of this
government and the States, or on the material at the FAA, call 781–238–7125.
PW4170, PW4168A–1D, PW4168–1D,
distribution of power and PW4164–1D, PW4164C–1D, and PW4164C/ (5) You may view this service information
responsibilities among the various B–1D turbofan engines with an HPC 10th that is incorporated by reference at the
levels of government. stage disk, P/N 53H976–06, with an S/N National Archives and Records
For the reasons discussed above, I listed Table 1 of PW ASB PW4G–100–A72– Administration (NARA). For information on
certify that this AD: 255, dated August 31, 2015, installed. the availability of this material at NARA, call
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202–741–6030, or go to: http:// FAA, Engine & Propeller Directorate, the IDG and the main fuel pump,
www.archives.gov/federal-register/cfr/ibr- 1200 District Avenue, Burlington, MA. without adequate protection. A total of
locations.html. For information on the availability of three burn-through events have
Issued in Burlington, Massachusetts, on this material at the FAA, call 781–238– occurred. The NPRM proposed to
April 7, 2016. 7125. It is also available on the Internet require replacing the accessory heat
Colleen M. D’Alessandro, at http://www.regulations.gov by shield assembly. We are issuing this AD
Manager, Engine & Propeller Directorate, searching for and locating Docket No. to prevent an uncontrolled engine fire,
Aircraft Certification Service. FAA–2015–4344. and damage to the airplane.
[FR Doc. 2016–09687 Filed 4–26–16; 8:45 am]
Examining the AD Docket Comments
BILLING CODE 4910–13–P
You may examine the AD docket on We gave the public the opportunity to
the Internet at http:// participate in developing this AD. The
DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for following presents the comments
and locating Docket No. FAA–2015– received on the NPRM (80 FR 75952,
Federal Aviation Administration 4344; or in person at the Docket December 7, 2015) and the FAA’s
Management Facility between 9 a.m. response to each comment.
14 CFR Part 39 and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket Support for the NPRM (80 FR 75952,
[Docket No. FAA–2015–4344; Directorate December 7, 2015)
Identifier 2015–NE–32–AD; Amendment 39– contains this AD, the regulatory
18486; AD 2016–08–10] evaluation, any comments received, and The Boeing Company and the
other information. The address for the National Transportation Safety Board
RIN 2120–AA64 Docket Office (phone: 800–647–5527) is expressed support for the NPRM (80 FR
Airworthiness Directives; General Document Management Facility, U.S. 75952, December 7, 2015).
Electric Company Turbofan Engines Department of Transportation, Docket
Operations, M–30, West Building Revision to Service Information
AGENCY: Federal Aviation Ground Floor, Room W12–140, 1200 We revised the Discussion section and
Administration (FAA), DOT. New Jersey Avenue SE., Washington, Applicability paragraph (e) of this AD to
ACTION: Final rule. DC 20590. include all the GE CF6–80C2 and CF6–
FOR FURTHER INFORMATION CONTACT: 80E1 turbofan engine models.
SUMMARY: We are adopting a new Herman Mak, Aerospace Engineer,
airworthiness directive (AD) for all Request To Change Summary
Engine Certification Office, FAA, Engine
General Electric Company (GE) CF6– & Propeller Directorate, 1200 District GE requested that we revise the
80C2A1, CF6–80C2A2, CF6–80C2A3, Avenue, Burlington, MA 01803; phone: Summary paragraph of this AD to
CF6–80C2A5, CF6–80C2A5F, CF6– 781–238–7147; fax: 781–238–7199; correct the number of events and clarify
80C2A8, CF6–80C2B1, CF6–80C2B1F, email: herman.mak@faa.gov. the event description.
CF6–80C2B1F1, CF6–80C2B1F2, CF6– We agree. Only three of the originally
SUPPLEMENTARY INFORMATION:
80C2B2, CF6–80C2B2F, CF6–80C2B3F, specified five events resulted in heat
CF6–80C2B4, CF6–80C2B4F, CF6– Discussion shield burn-throughs. We revised the
80C2B5F, CF6–80C2B6, CF6–80C2B6F, We issued a notice of proposed Summary paragraph of this AD to
CF6–80C2B6FA, CF6–80C2B7F, CF6– rulemaking (NPRM) to amend 14 CFR correct the number of events and clarify
80C2B8F, CF6–80C2D1F, CF6–80C2L1F, part 39 by adding an AD that would the event description.
CF6–80C2K1F and CF6–80E1A1, CF6– apply to GE CF6–80C2A1, CF6–80C2A2,
80E1A2, CF6–80E1A3, CF6–80E1A4, Request To Revise the Other Related
CF6–80C2A3, CF6–80C2A5, CF6– Service Information Paragraph
and CF6–80E1A4/B turbofan engines. 80C2A5F, CF6–80C2A8, CF6–80C2B1,
This AD was prompted by reports of a CF6–80C2B1F, CF6–80C2B1F1, CF6– GE requested that we revise the Other
burn-through of the accessory heat 80C2B1F2, CF6–80C2B2, CF6–80C2B2F, Related Service Information paragraph
shield during an engine fire, CF6–80C2B3F, CF6–80C2B4, CF6– of this AD to remove GE Service
propagating the fire into the accessory 80C2B4F, CF6–80C2B5F, CF6–80C2B6, Bulletin (SB) CF6–80C2 S/B 72–1523,
compartment and igniting additional CF6–80C2B6F, CF6–80C2B6FA, CF6– dated September 22, 2015. This SB only
flammable fuel source. This AD requires 80C2B7F, CF6–80C2B8F, CF6– applies to the military variant of the
replacing the accessory heat shield 80C2D1F, CF6–80C2L1F, and CF6– engine.
assembly. We are issuing this AD to 80C2K1F turbofan engines. This AD that We disagree. The military variant of
prevent fires from propagating into the would also apply to CF6–80E1A1, CF6– the engine is also certified by the FAA.
accessory compartment, resulting in an 80E1A2, CF6–80E1A3, CF6–80E1A4, We did not change this AD.
uncontrolled engine fire, and damage to and CF6–80E1A4/B turbofan engines.
the airplane. Request To Revise the Costs of
The NPRM published in the Federal Compliance
DATES: This AD is effective June 1, 2016. Register on December 7, 2015 (80 FR
The Director of the Federal Register 75952). The NPRM was prompted by GE, KLM Royal Dutch Airlines (KLM),
approved the incorporation by reference reports of a burn-through of the All Nippon Airways (ANA), and Federal
of certain publications listed in this AD accessory heat shield during an engine Express (FedEx) requested that we
as of June 1, 2016. fire leading to an accessory revise the Costs of Compliance
jstallworth on DSK7TPTVN1PROD with RULES
ADDRESSES: For service information compartment fire. A fire burns through paragraph of this AD to correct the parts
identified in this final rule, contact the accessory heat shield and ignites the cost used in the calculations.
General Electric Company, GE Aviation, integrated drive generator (IDG) and We agree. We considered the costs of
Room 285, 1 Neumann Way, Cincinnati, main fuel pump, which supports further all the parts needed to comply with this
OH 45215; phone: 513–552–3272; email: combustion. The existing accessory heat AD and revised the costs per engine to
aviation.fleetsupport@ge.com. You may shield assembly leaves a large area $14,207 and the total cost to U.S.
view this service information at the above the sensitive accessories, such as operators to $13,680,920.
VerDate Sep<11>2014 15:13 Apr 26, 2016 Jkt 238001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\27APR1.SGM 27APR1](https://thefederalregister.org/doc/81_FR_24777/page/4.svg)
Document Created: 2018-02-07 13:55:30
Document Modified: 2018-02-07 13:55:30
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective June 1, 2016. | |
| 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: [email protected] | |
| FR Citation | 81 FR 24696 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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