81 FR 19514 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 65 (April 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 65 (April 5, 2016)
| Page Range | 19514-19516 | |
| FR Document | 2016-07578 |
[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)] [Proposed Rules] [Pages 19514-19516] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-07578] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5041; Directorate Identifier 2015-NM-102-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 and 747-8F series airplanes. This proposed AD was prompted by a report that static strength analysis has shown that the aluminum transmission aft bearing plate assemblies have inadequate structural strength for one or more of the required load cases, including cases for drive system jam, flap skew, and structural damage tolerance. Inadequate structural strength can result in damage to the transmission aft bearing plate assemblies. This proposed AD would require removing aluminum transmission aft bearing plate assemblies from the flap track and installing titanium transmission aft bearing plate assemblies to the flap track. We are proposing this AD to prevent inadequate structural strength of transmission aft bearing plate assemblies. This condition could result in damaged transmission aft bearing plate assemblies, which could result in incorrect operation and departure of the flap from the airplane and consequent loss of controllability of the airplane. DATES: We must receive comments on this proposed AD by May 20, 2016. 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 Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5041. 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- [[Page 19515]] 5041; 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: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; 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-2016-5041; Directorate Identifier 2015-NM-102-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 have received a report that static strength analysis has shown that the aluminum transmission aft bearing plate assemblies have inadequate structural strength for one or more of the required load cases, including cases for drive system jam, flap skew, and structural damage tolerance. These types of load cases can cause a flap transmission torque brake to engage, which will then cause additional loading on the transmission aft bearing plate assemblies common to that flap. This could cause damage to the transmission aft bearing plate assemblies. This condition, if not corrected, could result in transmission aft bearing plate assemblies working incorrectly or departure of the flap from the airplane, which could result in loss of controllability of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-57A2348, dated June 12, 2015. The service information describes procedures for removing the aluminum transmission aft bearing plate assembly from the flap track and installing a new titanium transmission aft bearing plate assembly to the flap track. 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 accomplishing the actions specified in the service information described previously. Costs of Compliance We estimate that this proposed AD affects 11 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Replacement........................... 114 work-hours x $85 per $48,682 $58,372 $642,092 hour = $9,690. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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, 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: [[Page 19516]] 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): The Boeing Company: Docket No. FAA-2016-5041; Directorate Identifier 2015-NM-102-AD. (a) Comments Due Date We must receive comments by May 20, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747-8 and 747-8F series airplanes, certified in any category, as identified in Boeing Alert Service Bulletin 747-57A2348, dated June 12, 2015. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a report that static strength analysis has shown that the aluminum transmission aft bearing plate assemblies have inadequate structural strength for one or more of the required load cases, including cases for drive system jam, flap skew, and structural damage tolerance. Inadequate structural strength can result in damage to the transmission aft bearing plate assemblies. We are issuing this AD to prevent inadequate structural strength of transmission aft bearing plate assemblies. This condition could result in damaged transmission aft bearing plate assemblies, which could result in incorrect operation and departure of the flap from the airplane and consequent loss of controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement Within 48 months after the effective date of this AD: Remove aluminum transmission aft bearing plate assemblies from the flap track and install new titanium transmission aft bearing plate assemblies to the flap track, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-57A2348, dated June 12, 2015. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (i)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (h)(4)(i) and (h)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (i) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on March 24, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-07578 Filed 4-4-16; 8:45 am] BILLING CODE 4910-13-P
![19514 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules
widespread fatigue damage (WFD). We are deviation, or alteration deviation must meet AD was prompted by a report that static
issuing this AD to detect and correct fatigue the certification basis of the airplane and the strength analysis has shown that the
cracking around certain fastener locations approval must specifically refer to this AD. aluminum transmission aft bearing plate
that could cause multiple window corner (4) Except as required by paragraph (h) of
this AD: For service information that
assemblies have inadequate structural
skin cracks, which could result in rapid
decompression and consequent reduced contains steps that are labeled as RC, the strength for one or more of the required
structural integrity of the airplane. provisions of paragraphs (i)(4)(i) and (i)(4)(ii) load cases, including cases for drive
of this AD apply. system jam, flap skew, and structural
(f) Compliance (i) The steps labeled as RC, including damage tolerance. Inadequate structural
Comply with this AD within the substeps under an RC step and any figures strength can result in damage to the
compliance times specified, unless already identified in an RC step, must be done to transmission aft bearing plate
done. comply with the AD. An AMOC is required assemblies. This proposed AD would
for any deviations to RC steps, including
(g) Repetitive Inspections and Repair
substeps and identified figures.
require removing aluminum
At the applicable time specified in (ii) Steps not labeled as RC may be transmission aft bearing plate
paragraph 1.E., ‘‘Compliance,’’ of Boeing deviated from using accepted methods in assemblies from the flap track and
Alert Service Bulletin 737–53A1351, dated accordance with the operator’s maintenance installing titanium transmission aft
July 8, 2015: Do an external high frequency or inspection program without obtaining bearing plate assemblies to the flap
eddy current (HFEC) inspection for cracking approval of an AMOC, provided the RC steps, track. We are proposing this AD to
of the skin around the fastener locations at including substeps and identified figures, can prevent inadequate structural strength
the upper forward and lower aft corners of still be done as specified, and the airplane
each window between station (STA) 360 and
of transmission aft bearing plate
can be put back in an airworthy condition.
STA 540, as applicable, and at the lower assemblies. This condition could result
forward and upper aft corners of each (j) Related Information in damaged transmission aft bearing
window between STA 727 and STA 887, in (1) For more information about this AD, plate assemblies, which could result in
accordance with the Accomplishment contact Jason Deutschman, Aerospace incorrect operation and departure of the
Instructions of Boeing Alert Service Bulletin Engineer, Airframe Branch, ANM–120S, flap from the airplane and consequent
737–53A1351, dated July 8, 2015. Repeat the FAA, Seattle ACO, 1601 Lind Avenue SW., loss of controllability of the airplane.
inspection thereafter at the applicable times Renton, WA 98057–3356; phone: 425–917–
specified in paragraph 1.E., ‘‘Compliance,’’ of DATES: We must receive comments on
6595; fax: 425–917–6590; email:
Boeing Alert Service Bulletin 737–53A1351, jason.deutschman@faa.gov. this proposed AD by May 20, 2016.
dated July 8, 2015. If any crack is found (2) For service information identified in ADDRESSES: You may send comments,
during any inspection, repair before further this AD, contact Boeing Commercial using the procedures found in 14 CFR
flight using a method approved in Airplanes, Attention: Data & Services 11.43 and 11.45, by any of the following
accordance with the procedures specified in Management, P.O. Box 3707, MC 2H–65, methods:
paragraph (i) of this AD. Seattle, WA 98124–2207; telephone: 206–
• Federal eRulemaking Portal: Go to
544–5000, extension 1; fax: 206–766–5680;
(h) Exception to the Service Bulletin http://www.regulations.gov. Follow the
Internet: https://www.myboeingfleet.com.
Specifications instructions for submitting comments.
You may view the referenced service
Although Boeing Alert Service Bulletin information at the FAA, Transport Airplane • Fax: 202–493–2251.
737–53A1351, dated July 8, 2015, specifies to Directorate, 1601 Lind Avenue SW., Renton, • Mail: U.S. Department of
contact Boeing for repair instructions, and WA. For information on the availability of Transportation, Docket Operations, M–
specifies that action as ‘‘RC’’ (Required for this material at the FAA, call 425–227–1221. 30, West Building Ground Floor, Room
Compliance), this AD requires repair before
Issued in Renton, Washington, on March W12–140, 1200 New Jersey Avenue SE.,
further flight using a method approved in
accordance with the procedures specified in 24, 2016. Washington, DC 20590.
paragraph (i) of this AD. Michael Kaszycki, • Hand Delivery: Deliver to Mail
Acting Manager, Transport Airplane address above between 9 a.m. and 5
(i) Alternative Methods of Compliance p.m., Monday through Friday, except
(AMOCs) Directorate, Aircraft Certification Service.
[FR Doc. 2016–07577 Filed 4–4–16; 8:45 am] Federal holidays.
(1) The Manager, Seattle Aircraft For service information identified in
Certification Office (ACO), FAA, has the BILLING CODE 4910–13–P
this NPRM, contact Boeing Commercial
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
Airplanes, Attention: Data & Services
CFR 39.19. In accordance with 14 CFR 39.19, DEPARTMENT OF TRANSPORTATION Management, P.O. Box 3707, MC 2H–65,
send your request to your principal inspector Seattle, WA 98124–2207; telephone
or local Flight Standards District Office, as Federal Aviation Administration 206–544–5000, extension 1; fax 206–
appropriate. If sending information directly 766–5680; Internet https://
to the manager of the ACO, send it to the 14 CFR Part 39 www.myboeingfleet.com. You may view
attention of the person identified in this referenced service information at
paragraph (j)(1) of this AD. Information may [Docket No. FAA–2016–5041; Directorate
Identifier 2015–NM–102–AD] the FAA, Transport Airplane
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov.
Directorate, 1601 Lind Avenue SW.,
RIN 2120–AA64 Renton, WA. For information on the
(2) Before using any approved AMOC,
notify your appropriate principal inspector, availability of this material at the FAA,
Airworthiness Directives; The Boeing call 425–227–1221. It is also available
or lacking a principal inspector, the manager
of the local flight standards district office/ Company Airplanes on the Internet at http://
certificate holding district office. AGENCY: Federal Aviation www.regulations.gov by searching for
Lhorne on DSK5TPTVN1PROD with PROPOSALS
(3) An AMOC that provides an acceptable Administration (FAA), DOT. and locating Docket No. FAA–2016–
level of safety may be used for any repair, 5041.
modification, or alteration required by this ACTION: Notice of proposed rulemaking
AD if it is approved by the Boeing (NPRM). Examining the AD Docket
Commercial Airplanes Organization
Designation Authorization (ODA) that has SUMMARY: We propose to adopt a new You may examine the AD docket on
been authorized by the Manager, Seattle airworthiness directive (AD) for certain the Internet at http://
ACO, to make those findings. To be The Boeing Company Model 747–8 and www.regulations.gov by searching for
approved, the repair method, modification 747–8F series airplanes. This proposed and locating Docket No. FAA–2016–
VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\05APP1.SGM 05APP1](https://thefederalregister.org/doc/81_FR_19579/page/1.svg)
![19516 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules
PART 39—AIRWORTHINESS send your request to your principal inspector DEPARTMENT OF TRANSPORTATION
DIRECTIVES or local Flight Standards District Office, as
appropriate. If sending information directly Federal Aviation Administration
■ 1. The authority citation for part 39 to the manager of the ACO, send it to the
continues to read as follows: attention of the person identified in 14 CFR Part 39
Authority: 49 U.S.C. 106(g), 40113, 44701. paragraph (i)(1) of this AD. Information may
[Docket No. FAA–2016–4123; Directorate
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Identifier 2016–NE–06–AD]
§ 39.13 [Amended] Requests@faa.gov.
■ 2. The FAA amends § 39.13 by adding (2) Before using any approved AMOC, RIN 2120–AA64
the following new airworthiness notify your appropriate principal inspector,
or lacking a principal inspector, the manager Airworthiness Directives; International
directive (AD):
of the local flight standards district office/ Aero Engines AG Turbofan Engines
The Boeing Company: Docket No. FAA– certificate holding district office.
2016–5041; Directorate Identifier 2015– AGENCY: Federal Aviation
(3) An AMOC that provides an acceptable Administration (FAA), DOT.
NM–102–AD.
level of safety may be used for any repair,
(a) Comments Due Date ACTION: Notice of proposed rulemaking
modification, or alteration required by this
AD if it is approved by the Boeing (NPRM).
We must receive comments by May 20,
2016. Commercial Airplanes Organization SUMMARY: We propose to adopt a new
Designation Authorization (ODA) that has airworthiness directive (AD) for certain
(b) Affected ADs
been authorized by the Manager, Seattle International Aero Engines AG (IAE)
None. ACO, to make those findings. To be V2522–A5, V2524–A5, V2525–D5,
(c) Applicability approved, the repair method, modification V2527–A5, V2527E–A5, V2527M–A5,
This AD applies to The Boeing Company deviation, or alteration deviation must meet
V2528–D5, V2530–A5, and V2533–A5
Model 747–8 and 747–8F series airplanes, the certification basis of the airplane, and the
turbofan engines. This proposed AD was
certified in any category, as identified in approval must specifically refer to this AD.
prompted by the fracture of the high-
Boeing Alert Service Bulletin 747–57A2348, (4) For service information that contains
pressure turbine (HPT) stage 2 hub
dated June 12, 2015. steps that are labeled as Required for
during flight, which resulted in an in-
Compliance (RC), the provisions of
(d) Subject flight shutdown (IFSD), undercowl fire,
paragraphs (h)(4)(i) and (h)(4)(ii) of this AD
Air Transport Association (ATA) of apply.
and smoke in the cabin. This proposed
America Code 57, Wings.
(i) The steps labeled as RC, including
AD would require inspecting the HPT
(e) Unsafe Condition substeps under an RC step and any figures
stage 1 hub and HPT stage 2 hub, and,
identified in an RC step, must be done to if necessary, their replacement with
This AD was prompted by a report that parts that are eligible for installation.
static strength analysis has shown that the comply with the AD. An AMOC is required
aluminum transmission aft bearing plate for any deviations to RC steps, including We are proposing this AD to prevent
assemblies have inadequate structural substeps and identified figures. failure of the HPT stage 1 or HPT stage
strength for one or more of the required load (ii) Steps not labeled as RC may be 2 hubs, which could result in
cases, including cases for drive system jam, deviated from using accepted methods in uncontained HPT blade release, damage
flap skew, and structural damage tolerance. accordance with the operator’s maintenance to the engine, and damage to the
Inadequate structural strength can result in or inspection program without obtaining airplane.
damage to the transmission aft bearing plate
approval of an AMOC, provided the RC steps, DATES: We must receive comments on
assemblies. We are issuing this AD to prevent
including substeps and identified figures, can this proposed AD by June 6, 2016.
inadequate structural strength of
transmission aft bearing plate assemblies. still be done as specified, and the airplane ADDRESSES: You may send comments,
This condition could result in damaged can be put back in an airworthy condition. using the procedures found in 14 CFR
transmission aft bearing plate assemblies, (i) Related Information 11.43 and 11.45, by any of the following
which could result in incorrect operation and methods:
departure of the flap from the airplane and (1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
• Federal eRulemaking Portal: Go to
consequent loss of controllability of the
airplane. Airframe Branch, ANM–120S, FAA, Seattle
http://www.regulations.gov. Follow the
ACO, 1601 Lind Avenue SW., Renton, WA instructions for submitting comments.
(f) Compliance
98057–3356; phone: 425–917–6432; fax: 425– • Fax: 202–493–2251.
Comply with this AD within the 917–6590; email: bill.ashforth@faa.gov.
• Mail: U.S. Department of
compliance times specified, unless already (2) For service information identified in Transportation, Docket Operations, M–
done. 30, West Building Ground Floor, Room
this AD, contact Boeing Commercial
(g) Replacement Airplanes, Attention: Data & Services W12–140, 1200 New Jersey Avenue SE.,
Management, P.O. Box 3707, MC 2H–65, Washington, DC 20590.
Within 48 months after the effective date
Seattle, WA 98124–2207; telephone 206– • Hand Delivery: Deliver to Mail
of this AD: Remove aluminum transmission
aft bearing plate assemblies from the flap 544–5000, extension 1; fax 206–766–5680; address above between 9 a.m. and 5
track and install new titanium transmission Internet https://www.myboeingfleet.com. For p.m., Monday through Friday, except
aft bearing plate assemblies to the flap track, information on the availability of this Federal holidays.
in accordance with the Accomplishment material at the FAA, call 425–227–1221. For service information identified in
Instructions of Boeing Alert Service Bulletin this NPRM, contact International Aero
Issued in Renton, Washington, on March
Lhorne on DSK5TPTVN1PROD with PROPOSALS
747–57A2348, dated June 12, 2015. Engines AG, 400 Main Street, East
24, 2016. Hartford, CT 06118; phone: 860–368–
(h) Alternative Methods of Compliance
(AMOCs) Michael Kaszycki, 3700; fax: 860–368–4600; email:
(1) The Manager, Seattle Aircraft Acting Manager, Transport Airplane iaeinfo@iaev2500.com; Internet: https://
Certification Office (ACO), FAA, has the Directorate, Aircraft Certification Service. www.iaeworld.com. You may view this
authority to approve AMOCs for this AD, if [FR Doc. 2016–07578 Filed 4–4–16; 8:45 am] service information at the FAA, Engine
requested using the procedures found in 14 BILLING CODE 4910–13–P & Propeller Directorate, 1200 District
CFR 39.19. In accordance with 14 CFR 39.19, Avenue, Burlington, MA. For
VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\05APP1.SGM 05APP1](https://thefederalregister.org/doc/81_FR_19579/page/3.svg)
Document Created: 2018-02-07 13:53:54
Document Modified: 2018-02-07 13:53:54
| 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 May 20, 2016. | |
| Contact | Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 19514 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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