81 FR 74358 - Airworthiness Directives; Pratt & Whitney Division Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 207 (October 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 207 (October 26, 2016)
| Page Range | 74358-74360 | |
| FR Document | 2016-25799 |
[Federal Register Volume 81, Number 207 (Wednesday, October 26, 2016)] [Proposed Rules] [Pages 74358-74360] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-25799] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8836; Directorate Identifier 2016-NE-17-AD] RIN 2120-AA64 Airworthiness Directives; Pratt & Whitney Division Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, and PW4090-3 turbofan engines. This proposed AD was prompted by an uncontained failure of a high-pressure turbine (HPT) hub during takeoff. This proposed AD would require an inspection to measure the surface condition of the aft side web/rim fillet of HPT 1st stage hubs and removal from service of hubs that fail inspection. We are proposing this AD to prevent failure of the HPT 1st stage hub, uncontained hub release, damage to the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by December 12, 2016. [[Page 74359]] ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Pratt & Whitney Division, 400 Main St., East Hartford, CT 06118; phone: 800- 565-0140; fax: 860-565-5442. 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. 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-2016- 8836; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jo-Ann Theriault, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7105; fax: 781- 238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-8836; Directorate Identifier 2016-NE-07-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We received a report of an uncontained failure of an HPT hub during takeoff. The root cause of the event is a machining anomaly (cutter mismatch) in the aft web/rim fillet area of the HPT 1st stage hub. The machining mismatch raises the stress and significantly reduces the life of the hub. The defect was introduced when the part was originally manufactured. This condition, if not corrected, could result in failure of the HPT 1st stage hub, uncontained hub release, damage to the engine, and damage to the airplane. Related Service Information Under 1 CFR Part 51 We reviewed PW Service Bulletin (SB) PW4G-112-72-342, dated September 23, 2016. This PW SB provides guidance on performing the HPT 1st stage hub web/rim fillet replication inspection and measurement for the affected HPT hubs. 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. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require an inspection to measure the surface condition of the aft side web/rim fillet of HPT 1st stage hubs and removal from service of hubs that fail inspection. Costs of Compliance We estimate that this proposed AD affects 119 engines installed on airplanes of U.S. registry. We also estimate that it would take about 1 hour per engine to do the inspection. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $10,115. 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 We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: [[Page 74360]] 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): Pratt & Whitney Division: Docket No. FAA-2016-8836; Directorate Identifier 2016-NE-17-AD. (a) Comments Due Date We must receive comments by December 12, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, and PW4090-3 turbofan engines. (d) Unsafe Condition This AD was prompted by an uncontained failure of a high- pressure turbine (HPT) hub during takeoff. We are issuing this AD to prevent failure of the HPT 1st stage hub, uncontained hub 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) At the next engine shop visit after the effective date of this AD, perform the HPT 1st stage hub web/rim fillet replication inspection and measurement using the Accomplishment Instructions, Part A, paragraphs 2.A. and 2.B.(1) to 2.B.(4) or Part B, paragraphs 1.A. and 1.B.(1) to 1.B.(4), of PW Service Bulletin (SB) PW4G-112- 72-342, dated September 23, 2016. (2) If the hub fails inspection, remove the hub from service before further flight and replace with a part eligible for installation. (f) Definition For the purpose of this AD, an ``engine shop visit'' is the induction of an engine into the shop for maintenance involving the separation of any major mating flange, except that the separation of engine flanges solely for the purposes of transportation without subsequent maintenance does not constitute an engine shop visit. (g) Installation Prohibition After the effective date of this AD, do not install or re- install into any engine any HPT 1st stage hub that has not been inspected and passed the inspection required by paragraph (e) of this AD. (h) 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]. (i) Related Information (1) For more information about this AD, contact Jo-Ann Theriault, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7105; fax: 781-238-7199; email: [email protected]. (2) PW SB PW4G-112-72-342, dated September 23, 2016, can be obtained from PW using the contact information in paragraph (i)(3) of this AD. (3) For service information identified in this AD, contact Pratt & Whitney Division, 400 Main St., East Hartford, CT 06118; phone: 800-565-0140; fax: 860-565-5442. (4) 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. Issued in Burlington, Massachusetts, on October 19, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-25799 Filed 10-25-16; 8:45 am] BILLING CODE 4910-13-P
![74358 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
been embodied: Modify the outer wing, and effective date of this AD, whichever occurs changes to procedures or tests identified as
do all applicable related investigative and later. RC require approval of an AMOC.
corrective actions, in accordance with the (iii) For Model A300 B4–200 airplanes:
(l) Related Information
Accomplishment Instructions of Airbus Within 47,900 flight cycles since first flight
Mandatory Service Bulletin A300–57–0203, of the airplane, or within 4 months after the (1) Refer to Mandatory Continuing
Revision 04, dated February 18, 2015. effective date of this AD, whichever occurs Airworthiness Information (MCAI) EASA AD
(x) For airplanes on which Airbus later. 2015–0173, dated August 24, 2015, for
Mandatory Service Bulletin A300–57–0258, related information. You may examine the
(i) Service Information Exception MCAI on the Internet at http://
dated September 30, 2014, has not been
embodied: Modify the wing structure and do Where any service information identified www.regulations.gov by searching for and
all applicable related investigative and in table 1 to paragraphs (g), (h), and (i) of this locating Docket No. FAA–2016–9298.
corrective actions, in accordance with the AD specifies to contact the manufacturer for (2) For service information identified in
Accomplishment Instructions of Airbus instructions or solutions, before further this final rule, contact Airbus SAS,
Mandatory Service Bulletin A300–57–0258, flight, repair using a method approved by the Airworthiness Office–EAW, 1 Rond Point
dated September 30, 2014. Manager, International Branch, ANM–116, Maurice Bellonte, 31707 Blagnac Cedex,
(xi) For airplanes on which Airbus Transport Airplane Directorate, FAA; or the France; telephone: +33 5 61 93 36 96; fax:
Mandatory Service Bulletin A300–57–0259, European Aviation Safety Agency (EASA); or +33 5 61 93 44 51; email:
dated September 30, 2014, has not been Airbus’s EASA Design Organization continued.airworthiness-wb.external@
embodied: Modify the wing structure, and do Approval (DOA). airbus.com; Internet http://www.airbus.com.
all applicable related investigative and You may view this service information at the
(j) Terminating Action for Certain FAA, Transport Airplane Directorate, 1601
corrective actions, in accordance with the Requirements in AD 2004–23–20
Accomplishment Instructions of Airbus Lind Avenue SW., Renton, WA. For
Mandatory Service Bulletin A300–57–0259, Accomplishing the modification required information on the availability of this
dated September 30, 2014. by paragraph (h)(1)(iii) of this AD terminates material at the FAA, call 425–227–1221.
(2) If it is determined that Airbus Service the modification required by paragraph (i) of
Issued in Renton, Washington, on October
Bulletin A300–53–0374, Revision 04, dated AD 2004–23–20 for that airplane only.
13, 2016.
July 5, 2013 (mod 12794) has not been (k) Other FAA AD Provisions Michael Kaszycki,
embodied: Within the compliance time
The following provisions also apply to this Acting Manager, Transport Airplane
specified in paragraphs (h)(2)(i), (h)(2)(ii),
AD: Directorate, Aircraft Certification Service.
(h)(2)(iii), and (h)(2)(iv) of this AD, as
(1) Alternative Methods of Compliance [FR Doc. 2016–25662 Filed 10–25–16; 8:45 am]
applicable, modify the rear fuselage, in
(AMOCs): The Manager, International
accordance with the Accomplishment BILLING CODE 4910–13–P
Branch, ANM–116, Transport Airplane
Instructions of Airbus Service Bulletin A300–
Directorate, FAA, has the authority to
53–0374, Revision 04, dated July 5, 2013,
approve AMOCs for this AD, if requested
except as required by paragraph (i) of this DEPARTMENT OF TRANSPORTATION
using the procedures found in 14 CFR 39.19.
AD. In accordance with 14 CFR 39.19, send your
(i) For Model A300 B2 and A300 B4–100 request to your principal inspector or local Federal Aviation Administration
airplanes, fuselage frame (FR) 55: Within Flight Standards District Office, as
31,300 flight cycles since first flight of the appropriate. If sending information directly 14 CFR Part 39
airplane, or within 4 months after the to the International Branch, send it to ATTN:
effective date of this AD, whichever occurs Dan Rodina, Aerospace Engineer, [Docket No. FAA–2016–8836; Directorate
later. International Branch, ANM–116, Transport Identifier 2016–NE–17–AD]
(ii) For Model A300 B2 and A300 B4–100 Airplane Directorate, FAA, 1601 Lind
airplanes, FR 58: Within 49,700 flight cycles RIN 2120–AA64
Avenue SW., Renton, WA 98057–3356;
since first flight of the airplane, or within 4 telephone 425–227–1405; fax 425–227–2125.
months after the effective date of this AD, Airworthiness Directives; Pratt &
Information may be emailed to: 9-ANM-116- Whitney Division Turbofan Engines
whichever occurs later. AMOC-REQUESTS@faa.gov. Before using
(iii) For Model A300 B4–200 airplanes, FR any approved AMOC, notify your appropriate AGENCY: Federal Aviation
55: Within 33,600 flight cycles since first principal inspector, or lacking a principal Administration (FAA), DOT.
flight of the airplane, or within 4 months inspector, the manager of the local flight
after the effective date of this AD, whichever ACTION: Notice of proposed rulemaking
standards district office/certificate holding
occurs later. district office. The AMOC approval letter (NPRM).
(iv) For Model A300 B4–200 airplanes, FR must specifically reference this AD.
58: Within 55,800 flight cycles since first SUMMARY: We propose to adopt a new
(2) Contacting the Manufacturer: For any
flight of the airplane, or within 4 months requirement in this AD to obtain corrective
airworthiness directive (AD) for all Pratt
after the effective date of this AD, whichever actions from a manufacturer, the action must & Whitney Division (PW) PW4074,
occurs later. be accomplished using a method approved PW4074D, PW4077, PW4077D,
(3) If it is determined that Airbus Service by the Manager, International Branch, ANM– PW4084, PW4084D, PW4090, and
Bulletin A300–53–0373, Revision 03, dated 116, Transport Airplane Directorate, FAA; or PW4090–3 turbofan engines. This
September 1, 2010 (mod 12796) has not been EASA; or Airbus’s EASA DOA. If approved proposed AD was prompted by an
embodied: Within the compliance time by the DOA, the approval must include the uncontained failure of a high-pressure
specified in paragraphs (h)(3)(i), (h)(3)(ii), DOA-authorized signature.
and (h)(3)(iii) of this AD, as applicable,
turbine (HPT) hub during takeoff. This
(3) Required for Compliance (RC): If any
modify the rear fuselage, in accordance with service information contains procedures or
proposed AD would require an
the Accomplishment Instructions of Airbus tests that are identified as RC, those inspection to measure the surface
Service Bulletin A300–53–0373, Revision 03, procedures and tests must be done to comply condition of the aft side web/rim fillet
dated September 1, 2010, except as required with this AD; any procedures or tests that are of HPT 1st stage hubs and removal from
by paragraph (i) of this AD. not identified as RC are recommended. Those service of hubs that fail inspection. We
Lhorne on DSK30JT082PROD with PROPOSALS
(i) For Model A300 B2 airplanes: Within procedures and tests that are not identified are proposing this AD to prevent failure
42,700 flight cycles since first flight of the as RC may be deviated from using accepted of the HPT 1st stage hub, uncontained
airplane, or within 4 months after the methods in accordance with the operator’s hub release, damage to the engine, and
effective date of this AD, whichever occurs maintenance or inspection program without
later. obtaining approval of an AMOC, provided
damage to the airplane.
(ii) For Model A300 B4–100 airplanes: the procedures and tests identified as RC can DATES: We must receive comments on
Within 41,700 flight cycles since first flight be done and the airplane can be put back in this proposed AD by December 12,
of the airplane, or within 4 months after the an airworthy condition. Any substitutions or 2016.
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![74360 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules
Authority: 49 U.S.C. 106(g), 40113, 44701. Engineer, Engine Certification Office, FAA, 11.43 and 11.45, by any of the following
Engine & Propeller Directorate, 1200 District methods:
§ 39.13 [Amended] Avenue, Burlington, MA 01803; phone: 781– • Federal eRulemaking Portal: Go to
■ 2. The FAA amends § 39.13 by adding 238–7105; fax: 781–238–7199; email: jo- http://www.regulations.gov. Follow the
the following new airworthiness ann.theriault@faa.gov.
(2) PW SB PW4G–112–72–342, dated
instructions for submitting comments.
directive (AD): • Fax: 202–493–2251.
September 23, 2016, can be obtained from
Pratt & Whitney Division: Docket No. FAA– PW using the contact information in • Mail: U.S. Department of
2016–8836; Directorate Identifier 2016– paragraph (i)(3) of this AD. Transportation, Docket Operations, M–
NE–17–AD. (3) For service information identified in 30, West Building Ground Floor, Room
(a) Comments Due Date this AD, contact Pratt & Whitney Division, W12–140, 1200 New Jersey Avenue SE.,
400 Main St., East Hartford, CT 06118; Washington, DC 20590.
We must receive comments by December
12, 2016.
phone: 800–565–0140; fax: 860–565–5442. • Hand Delivery: Deliver to Mail
(4) You may view this service information address above between 9 a.m. and 5
(b) Affected ADs at the FAA, Engine & Propeller Directorate,
1200 District Avenue, Burlington, MA. For
p.m., Monday through Friday, except
None. Federal holidays.
information on the availability of this
(c) Applicability material at the FAA, call 781–238–7125. For service information identified in
this NPRM, contact Bombardier, Inc., Q-
This AD applies to all Pratt & Whitney
Issued in Burlington, Massachusetts, on Series Technical Help Desk, 123 Garratt
Division (PW) PW4074, PW4074D, PW4077,
October 19, 2016. Boulevard, Toronto, Ontario M3K 1Y5,
PW4077D, PW4084, PW4084D, PW4090, and
PW4090–3 turbofan engines. Colleen M. D’Alessandro, Canada; telephone 416–375–4000; fax
Manager, Engine & Propeller Directorate, 416–375–4539; email thd.qseries@
(d) Unsafe Condition Aircraft Certification Service. aero.bombardier.com; Internet http://
This AD was prompted by an uncontained [FR Doc. 2016–25799 Filed 10–25–16; 8:45 am] www.bombardier.com. You may view
failure of a high-pressure turbine (HPT) hub this referenced service information at
BILLING CODE 4910–13–P
during takeoff. We are issuing this AD to the FAA, Transport Airplane
prevent failure of the HPT 1st stage hub,
uncontained hub release, damage to the
Directorate, 1601 Lind Avenue SW.,
engine, and damage to the airplane. DEPARTMENT OF TRANSPORTATION Renton, WA. For information on the
availability of this material at the FAA,
(e) Compliance Federal Aviation Administration call 425–227–1221.
Comply with this AD within the
compliance times specified, unless already 14 CFR Part 39 Examining the AD Docket
done. You may examine the AD docket on
(1) At the next engine shop visit after the [Docket No. FAA–2016–9299; Directorate the Internet at http://
effective date of this AD, perform the HPT 1st Identifier 2016–NM–119–AD]
www.regulations.gov by searching for
stage hub web/rim fillet replication
inspection and measurement using the RIN 2120–AA64 and locating Docket No. FAA–2016–
Accomplishment Instructions, Part A, 9299; or in person at the Docket
paragraphs 2.A. and 2.B.(1) to 2.B.(4) or Part Airworthiness Directives; Bombardier, Management Facility between 9 a.m.
B, paragraphs 1.A. and 1.B.(1) to 1.B.(4), of Inc. Airplanes and 5 p.m., Monday through Friday,
PW Service Bulletin (SB) PW4G–112–72– except Federal holidays. The AD docket
342, dated September 23, 2016. AGENCY: Federal Aviation contains this proposed AD, the
(2) If the hub fails inspection, remove the Administration (FAA), DOT. regulatory evaluation, any comments
hub from service before further flight and ACTION: Notice of proposed rulemaking received, and other information. The
replace with a part eligible for installation. (NPRM). street address for the Docket Operations
(f) Definition office (telephone 800–647–5527) is in
SUMMARY: We propose to adopt a new the ADDRESSES section. Comments will
For the purpose of this AD, an ‘‘engine
shop visit’’ is the induction of an engine into
airworthiness directive (AD) for certain be available in the AD docket shortly
the shop for maintenance involving the Bombardier Inc. Model DHC–8–102, after receipt.
separation of any major mating flange, except –103, and –106 airplanes; DHC–8–200
FOR FURTHER INFORMATION CONTACT:
that the separation of engine flanges solely series airplanes; and Model DHC–8–300
Morton Lee, Aerospace Engineer,
for the purposes of transportation without series airplanes. This proposed AD was
subsequent maintenance does not constitute
Propulsion and Services Branch, ANE–
prompted by reports of incorrect
an engine shop visit. 173, FAA, New York Aircraft
installation of the auto-ignition system
Certification Office, 1600 Stewart
(g) Installation Prohibition due to crossed wires at one of the
Avenue, Suite 410, Westbury, NY
After the effective date of this AD, do not
splices in the auto-relight system. This
11590; telephone 516–228–7355; fax
install or re-install into any engine any HPT proposed AD would require inspecting
516–794–5531.
1st stage hub that has not been inspected and the auto-ignition system for correct
wiring, and doing corrective actions if SUPPLEMENTARY INFORMATION:
passed the inspection required by paragraph
(e) of this AD. necessary. We are proposing this AD to Comments Invited
(h) Alternative Methods of Compliance
detect and correct incorrect wiring of
the auto-ignition system, which could We invite you to send any written
(AMOCs) relevant data, views, or arguments about
result in inability to restart the engine
The Manager, Engine Certification Office, this proposed AD. Send your comments
Lhorne on DSK30JT082PROD with PROPOSALS
FAA, may approve AMOCs for this AD. Use
in flight and consequent reduced
controllability of the airplane. to an address listed under the
the procedures found in 14 CFR 39.19 to ADDRESSES section. Include ‘‘Docket No.
make your request. You may email your DATES: We must receive comments on
FAA–2016–9299; Directorate Identifier
request to: ANE-AD-AMOC@faa.gov. this proposed AD by December 12, 2016–NM–119–AD’’ at the beginning of
(i) Related Information 2016. your comments. We specifically invite
(1) For more information about this AD, ADDRESSES: You may send comments, comments on the overall regulatory,
contact Jo-Ann Theriault, Aerospace using the procedures found in 14 CFR economic, environmental, and energy
VerDate Sep<11>2014 15:05 Oct 25, 2016 Jkt 241001 PO 00000 Frm 00046 Fmt 4702 Sfmt 4702 E:\FR\FM\26OCP1.SGM 26OCP1](https://thefederalregister.org/doc/81_FR_74565/page/3.svg)
Document Created: 2016-10-26 02:17:45
Document Modified: 2016-10-26 02:17:45
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by December 12, 2016. | |
| Contact | Jo-Ann Theriault, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7105; fax: 781- 238-7199; email: [email protected] | |
| FR Citation | 81 FR 74358 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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