80 FR 24195 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 83 (April 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 83 (April 30, 2015)
| Page Range | 24195-24198 | |
| FR Document | 2015-09805 |
[Federal Register Volume 80, Number 83 (Thursday, April 30, 2015)] [Rules and Regulations] [Pages 24195-24198] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-09805] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0286; Directorate Identifier 2014-NM-004-AD; Amendment 39-18145; AD 2015-08-09] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600 and -700 series airplanes. This AD was prompted by reports of cracking in the body station (STA) 727 bulkhead lower frame. This AD requires a detailed and open hole high frequency eddy current (HFEC) inspection of the left- and right-side lower frame webs and inner chords for cracking, and corrective actions and preventative modifications if necessary. This AD also provides for optional terminating action of the repetitive inspections, under certain conditions. We are issuing this AD to detect and correct cracking in a bulkhead lower frame web and inner chord, which could result in a severed frame and induced skin cracks, and could lead to rapid decompression of the fuselage. DATES: This AD is effective June 4, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 4, 2015. ADDRESSES: 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. 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-2014- 0286. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014- 0286; 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 Docket 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: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; 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 The Boeing Company Model 737-600 and -700 series airplanes. The NPRM published in the Federal Register on May 28, 2014 (79 FR 30490). The NPRM was prompted by reports of cracking in the body STA 727 bulkhead lower frame. The NPRM proposed to require a detailed and open hole high frequency eddy current (HFEC) inspection of the left- and right-side lower frame webs and inner chords for cracking, as applicable, and corrective actions and preventative modifications if necessary. The NPRM also proposed to provide for an optional terminating action for the repetitive inspections under certain conditions. We are issuing this AD to detect and correct cracking in a bulkhead lower frame web and inner chord, which could result in a severed frame and induced skin cracks, and could lead to rapid decompression of the fuselage. Comments We gave the public the opportunity to participate in developing this AD. Boeing and United Airlines stated that they support the NPRM (79 FR 30490, May 28, 2014). The following presents the comments received on the NPRM, and the FAA's response to each comment. Request To Clarify Modification and Repair Requirements Southwest Airlines (SWA) requested that we clarify whether the preventative modifications and repairs of the lower frame webs and inner chords (if [[Page 24196]] accomplished) must be done on both the left and right sides at the same time. SWA stated that paragraph (h) of the NPRM (79 FR 30490, May 28, 2014) reads, ``Accomplishment of a modification or a repair, in accordance with Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, terminates the repetitive inspections in this AD for the repaired or modified side only.'' SWA stated that Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, provides that for each airplane group, if a repair is installed on one side, a preventative modification must be installed on the opposing side. SWA also stated that, for airplanes with no cracks, a preventative modification is optional, but that the service information specifies that in this situation, both sides must be modified. We agree that clarification is necessary. Groups 2 and 3 airplanes are comprised of four airplanes on which a repair to the left side was installed prior to the issuance of Boeing Alert Service Bulletin 737- 53A1325, dated December 3, 2013. Therefore, SWA's comments are primarily for Group 1 airplanes. As specified in Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, if a crack is found on one side, then that side must be repaired and the preventative modification concurrently installed on the other side, even if that other side is not cracked. We also agree that if no cracking is found on either side and the operator chooses to install the preventative modification, then both sides must be modified, as specified in paragraph 3.B., Part 2, Step 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1325, dated December 3, 2013. Installing the preventative modification terminates the repetitive inspections. We have removed the wording ``for the repaired or modified side only'' from paragraph (h) of this AD. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the supplemental type certificate (STC) ST00830SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/rgstc.nsf/0/ 932b6080caa1856e86257d6c005c5a37/$FILE/ST00830SE.pdf) does not affect the actions specified in the NPRM (79 FR 30490, May 28, 2014). We concur with the commenter. We have redesignated paragraph (c) of the NPRM (79 FR 30490, May 28, 2014) as paragraph (c)(1) and added new paragraph (c)(2) to this AD to state that installation of STC ST00830SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ 932b6080caa1856e86257d6c005c5a37/$FILE/ST00830SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. 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, and minor editorial changes. We have determined that these minor changes:[Agr]re consistent with the intent that was proposed in the NPRM (79 FR 30490, May 28, 2014) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 30490, May 28, 2014). 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 Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013. The service information describes procedures for a detailed and open hole HFEC inspection of the left- and right-side lower frame webs and inner chords for cracking, and corrective actions and preventative modifications if necessary. The service information also provides for an optional terminating action of the repetitive inspections, under certain conditions. This service information is reasonably available at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0286. Or see ADDRESSES for other ways to access this service information. Costs of Compliance We estimate that this AD affects 489 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspections......................... 37 work-hours x $85 per $0 $3,145 $1,537,905 hour = $3,145. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the inspections. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair (per side)............................. 11 work-hours x $85 per hour = $2,820 $3,755 $935. Modification.................................. 17 work-hours x $85 per hour = 1,132 2,577 $1,445. ---------------------------------------------------------------------------------------------------------------- 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 [[Page 24197]] promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 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): 2015-08-09 The Boeing Company: Amendment 39-18145; Docket No. FAA- 2014-0286; Directorate Identifier 2014-NM-004-AD. (a) Effective Date This AD is effective June 4, 2015. (b) Affected ADs None. (c) Applicability (1) This AD applies to The Boeing Company Model 737-600 and -700 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013. (2) Installation of Supplemental Type Certificate (STC) ST00830SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/932b6080caa1856e86257d6c005c5a37/$FILE/ST00830SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST00830SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracking in the body station 727 bulkhead lower frame. We are issuing this AD to detect and correct cracking in a bulkhead lower frame web and inner chord, which could result in a severed framed and induced skin cracks, and could lead to rapid decompression of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections At the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, except as provided by paragraph (i)(1) of this AD: Do a detailed and open hole high frequency eddy current (HFEC) inspection of the left- and right-side lower frame webs and inner chords for cracking, as applicable, and do all applicable corrective actions and preventative modifications, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1325, dated December 3, 2013, except as required by paragraph (i)(2) of this AD. Repeat the applicable inspections required by this paragraph thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013. Do all applicable corrective actions and preventative modifications before further flight. (h) Terminating Action Accomplishment of a modification or a repair, in accordance with Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, terminates the repetitive inspections required by this AD. (i) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, specifies to contact Boeing for appropriate action: Before further flight, accomplish the corresponding action using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) Post-Repair Inspections The post-repair inspections specified in tables 4, 5, and 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, are not required by this AD. Note 1 to paragraph (j) of this AD: The damage tolerance inspections specified in tables 4, 5, and 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, may be used in support of compliance with Section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013, are not required by this AD. (k) 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 (l) 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 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. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (l) Related Information For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected]. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this [[Page 24198]] 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) Boeing Alert Service Bulletin 737-53A1325, dated December 3, 2013. (ii) Reserved. (3) For Boeing 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. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on April 13, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-09805 Filed 4-29-15; 8:45 am] BILLING CODE 4910-13-P
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The Special Conditions DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
Accordingly, pursuant to the Federal Aviation Administration except Federal holidays. The AD docket
authority delegated to me by the
contains this AD, the regulatory
Administrator, the following special 14 CFR Part 39 evaluation, any comments received, and
conditions are issued as part of the type
[Docket No. FAA–2014–0286; Directorate other information. The address for the
certification basis for Airbus Model
Identifier 2014–NM–004–AD; Amendment Docket Office (phone: 800–647–5527) is
SAneo series airplanes.
39–18145; AD 2015–08–09] Docket Management Facility, U.S.
In lieu of § 25.361(b), the following Department of Transportation, Docket
special conditions apply: RIN 2120–AA64
Operations, M–30, West Building
1. For turbine engine installations, the Ground Floor, Room W12–140, 1200
engine mounts, pylons, and adjacent Airworthiness Directives; The Boeing
Company Airplanes New Jersey Avenue SE., Washington,
supporting airframe structure must be DC 20590.
designed to withstand 1g level flight AGENCY: Federal Aviation
loads acting simultaneously with the FOR FURTHER INFORMATION CONTACT:
Administration (FAA), DOT. Alan Pohl, Aerospace Engineer,
maximum torque limit loads imposed
ACTION: Final rule. Airframe Branch, ANM–120S, FAA,
by each of the following:
a. Sudden engine deceleration due to Seattle Aircraft Certification Office,
SUMMARY: We are adopting a new
a malfunction that could result in a 1601 Lind Avenue SW., Renton, WA
airworthiness directive (AD) for certain
temporary loss of power or thrust; and 98057–3356; phone: 425–917–6450; fax:
The Boeing Company Model 737–600
425–917–6590; email: alan.pohl@
b. the maximum acceleration of the and –700 series airplanes. This AD was
faa.gov.
engine. prompted by reports of cracking in the
2. For auxiliary power-unit body station (STA) 727 bulkhead lower SUPPLEMENTARY INFORMATION:
installations, the power-unit mounts frame. This AD requires a detailed and
open hole high frequency eddy current Discussion
and adjacent supporting airframe
structure must be designed to withstand (HFEC) inspection of the left- and right- We issued a notice of proposed
1g level flight loads acting side lower frame webs and inner chords rulemaking (NPRM) to amend 14 CFR
simultaneously with the maximum for cracking, and corrective actions and part 39 by adding an AD that would
torque limit loads imposed by each of preventative modifications if necessary. apply to certain The Boeing Company
the following: This AD also provides for optional Model 737–600 and –700 series
a. Sudden auxiliary power-unit terminating action of the repetitive airplanes. The NPRM published in the
deceleration due to malfunction or inspections, under certain conditions. Federal Register on May 28, 2014 (79
structural failure; and We are issuing this AD to detect and FR 30490). The NPRM was prompted by
b. the maximum acceleration of the correct cracking in a bulkhead lower reports of cracking in the body STA 727
power unit. frame web and inner chord, which bulkhead lower frame. The NPRM
3. For engine supporting structure, an could result in a severed frame and proposed to require a detailed and open
ultimate loading condition must be induced skin cracks, and could lead to hole high frequency eddy current
considered that combines 1g flight loads rapid decompression of the fuselage. (HFEC) inspection of the left- and right-
with the transient dynamic loads DATES: This AD is effective June 4, 2015. side lower frame webs and inner chords
resulting from: The Director of the Federal Register for cracking, as applicable, and
a. The loss of any fan, compressor, or approved the incorporation by reference corrective actions and preventative
turbine blade; and separately, of a certain publication listed in this AD modifications if necessary. The NPRM
as of June 4, 2015. also proposed to provide for an optional
b. where applicable to a specific
ADDRESSES: For service information terminating action for the repetitive
engine design, any other engine
identified in this AD, contact Boeing inspections under certain conditions.
structural failure that results in higher
Commercial Airplanes, Attention: Data We are issuing this AD to detect and
loads.
& Services Management, P.O. Box 3707, correct cracking in a bulkhead lower
4. The ultimate loads developed from frame web and inner chord, which
the conditions specified in Special MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1; could result in a severed frame and
Conditions 3.a. and 3.b., above, are to be induced skin cracks, and could lead to
multiplied by a factor of 1.0 when fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view rapid decompression of the fuselage.
applied to engine mounts and pylons;
and multiplied by a factor of 1.25 when this referenced service information at Comments
applied to adjacent supporting airframe the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., We gave the public the opportunity to
structure.
Renton, WA. For information on the participate in developing this AD.
5. The airplane must be capable of Boeing and United Airlines stated that
continued safe flight considering the availability of this material at the FAA,
call 425–227–1221. It is also available they support the NPRM (79 FR 30490,
aerodynamic effects on controllability May 28, 2014). The following presents
due to any permanent deformation that on the Internet at http://
www.regulations.gov by searching for the comments received on the NPRM,
results from the conditions specified in and the FAA’s response to each
Special Condition 3, above. and locating Docket No. FAA–2014–
0286. comment.
Issued in Renton, Washington, on April 19,
rmajette on DSK2VPTVN1PROD with RULES
2015. Examining the AD Docket Request To Clarify Modification and
Victor Wicklund, Repair Requirements
You may examine the AD docket on
Acting Manager, Transport Airplane the Internet at http:// Southwest Airlines (SWA) requested
Directorate, Aircraft Certification Service. www.regulations.gov by searching for that we clarify whether the preventative
[FR Doc. 2015–10098 Filed 4–29–15; 8:45 am] and locating Docket No. FAA–2014– modifications and repairs of the lower
BILLING CODE 4910–13–P 0286; or in person at the Docket frame webs and inner chords (if
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promoting safe flight of civil aircraft in (c) Applicability this AD requires compliance within the
air commerce by prescribing regulations (1) This AD applies to The Boeing specified compliance time after the effective
for practices, methods, and procedures Company Model 737–600 and -700 series date of this AD.
airplanes, certificated in any category, as (2) Where Boeing Alert Service Bulletin
the Administrator finds necessary for 737–53A1325, dated December 3, 2013,
safety in air commerce. This regulation identified in Boeing Alert Service Bulletin
737–53A1325, dated December 3, 2013. specifies to contact Boeing for appropriate
is within the scope of that authority action: Before further flight, accomplish the
(2) Installation of Supplemental Type
because it addresses an unsafe condition Certificate (STC) ST00830SE (http:// corresponding action using a method
that is likely to exist or develop on rgl.faa.gov/Regulatory_and_Guidance_ approved in accordance with the procedures
products identified in this rulemaking Library/rgstc.nsf/0/ specified in paragraph (k) of this AD.
action. 932b6080caa1856e86257d6c005c5a37/ (j) Post-Repair Inspections
$FILE/ST00830SE.pdf) does not affect the
Regulatory Findings ability to accomplish the actions required by The post-repair inspections specified in
this AD. Therefore, for airplanes on which tables 4, 5, and 6 of paragraph 1.E.,
This AD will not have federalism ‘‘Compliance,’’ of Boeing Alert Service
STC ST00830SE is installed, a ‘‘change in
implications under Executive Order product’’ alternative method of compliance Bulletin 737–53A1325, dated December 3,
13132. This AD will not have a (AMOC) approval request is not necessary to 2013, are not required by this AD.
substantial direct effect on the States, on comply with the requirements of 14 CFR Note 1 to paragraph (j) of this AD: The
the relationship between the national 39.17. damage tolerance inspections specified in
government and the States, or on the tables 4, 5, and 6 of paragraph 1.E.,
(d) Subject ‘‘Compliance,’’ of Boeing Alert Service
distribution of power and
responsibilities among the various Air Transport Association (ATA) of Bulletin 737–53A1325, dated December 3,
America Code 53, Fuselage. 2013, may be used in support of compliance
levels of government. with Section 121.1109(c)(2) or 129.109(b)(2)
For the reasons discussed above, I (e) Unsafe Condition
of the Federal Aviation Regulations (14 CFR
certify that this AD: This AD was prompted by reports of 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The
(1) Is not a ‘‘significant regulatory cracking in the body station 727 bulkhead corresponding actions specified in the
action’’ under Executive Order 12866, lower frame. We are issuing this AD to detect Accomplishment Instructions of Boeing Alert
and correct cracking in a bulkhead lower Service Bulletin 737–53A1325, dated
(2) Is not a ‘‘significant rule’’ under frame web and inner chord, which could December 3, 2013, are not required by this
DOT Regulatory Policies and Procedures result in a severed framed and induced skin AD.
(44 FR 11034, February 26, 1979), cracks, and could lead to rapid
(3) Will not affect intrastate aviation decompression of the fuselage. (k) Alternative Methods of Compliance
in Alaska, and (AMOCs)
(f) Compliance
(4) Will not have a significant (1) The Manager, Seattle Aircraft
Comply with this AD within the
economic impact, positive or negative, Certification Office (ACO), FAA, has the
compliance times specified, unless already
authority to approve AMOCs for this AD, if
on a substantial number of small entities done.
requested using the procedures found in 14
under the criteria of the Regulatory (g) Inspections CFR 39.19. In accordance with 14 CFR 39.19,
Flexibility Act. send your request to your principal inspector
At the applicable times specified in
List of Subjects in 14 CFR Part 39 paragraph 1.E., ‘‘Compliance,’’ of Boeing or local Flight Standards District Office, as
Alert Service Bulletin 737–53A1325, dated appropriate. If sending information directly
Air transportation, Aircraft, Aviation December 3, 2013, except as provided by to the manager of the ACO, send it to the
safety, Incorporation by reference, paragraph (i)(1) of this AD: Do a detailed and attention of the person identified in
Safety. open hole high frequency eddy current paragraph (l) of this AD. Information may be
(HFEC) inspection of the left- and right-side emailed to: 9-ANM-Seattle-ACO-AMOC-
Adoption of the Amendment lower frame webs and inner chords for Requests@faa.gov.
cracking, as applicable, and do all applicable (2) Before using any approved AMOC,
Accordingly, under the authority notify your appropriate principal inspector,
corrective actions and preventative
delegated to me by the Administrator, modifications, in accordance with the or lacking a principal inspector, the manager
the FAA amends 14 CFR part 39 as Accomplishment Instructions of Boeing Alert of the local flight standards district office/
follows: Service Bulletin 737–53A1325, dated certificate holding district office.
December 3, 2013, except as required by (3) An AMOC that provides an acceptable
PART 39—AIRWORTHINESS paragraph (i)(2) of this AD. Repeat the level of safety may be used for any repair
DIRECTIVES applicable inspections required by this required by this AD if it is approved by the
paragraph thereafter at the applicable Boeing Commercial Airplanes Organization
■ 1. The authority citation for part 39 intervals specified in paragraph 1.E., Designation Authorization (ODA) that has
continues to read as follows: ‘‘Compliance,’’ of Boeing Alert Service been authorized by the Manager, Seattle
Bulletin 737–53A1325, dated December 3, ACO, to make those findings. For a repair
Authority: 49 U.S.C. 106(g), 40113, 44701. 2013. Do all applicable corrective actions and method to be approved, the repair must meet
preventative modifications before further the certification basis of the airplane, and the
§ 39.13 [Amended] approval must specifically refer to this AD.
flight.
■ 2. The FAA amends § 39.13 by adding (h) Terminating Action (l) Related Information
the following new airworthiness For more information about this AD,
Accomplishment of a modification or a
directive (AD): repair, in accordance with Boeing Alert contact Alan Pohl, Aerospace Engineer,
2015–08–09 The Boeing Company: Service Bulletin 737–53A1325, dated Airframe Branch, ANM–120S, FAA, Seattle
Amendment 39–18145; Docket No. December 3, 2013, terminates the repetitive Aircraft Certification Office, 1601 Lind
FAA–2014–0286; Directorate Identifier inspections required by this AD. Avenue SW., Renton, WA 98057–3356;
rmajette on DSK2VPTVN1PROD with RULES
2014–NM–004–AD. phone: 425–917–6450; fax: 425–917–6590;
(i) Exceptions to Service Information email: alan.pohl@faa.gov.
(a) Effective Date Specifications
(1) Where Boeing Alert Service Bulletin (m) Material Incorporated by Reference
This AD is effective June 4, 2015.
737–53A1325, dated December 3, 2013, (1) The Director of the Federal Register
(b) Affected ADs specifies a compliance time ‘‘after the approved the incorporation by reference
None. original issue date of this service bulletin,’’ (IBR) of the service information listed in this
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![24198 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations
paragraph under 5 U.S.C. 552(a) and 1 CFR mechanical actuator and release MCAI’’), to correct an unsafe condition
part 51. mechanism of the alternate extension for certain Bombardier, Inc. Model CL–
(2) You must use this service information system for the nose landing gear and 600–2E25 (Regional Jet Series 1000)
as applicable to do the actions required by main landing gear. We are issuing this airplanes. The MCAI states:
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737–
AD to prevent failure of the alternate During a design review, an error was
53A1325, dated December 3, 2013. release system of the landing gear, identified which led to the development of
(ii) Reserved. which could prevent the landing gear a new certification maintenance requirement
(3) For Boeing service information from extending during a failure of the (CMR) task. Without an effective
identified in this AD, contact Boeing normal landing gear extension system. maintenance task to maintain the aeroplane’s
Commercial Airplanes, Attention: Data & DATES: This AD becomes effective June inherent level of safety, there is a potential
Services Management, P.O. Box 3707, MC that a dormant failure of the alternate release
4, 2015. system of the landing gear could occur.
2H–65, Seattle, WA 98124–2207; telephone The Director of the Federal Register
206–544–5000, extension 1; fax 206–766– Failure of the landing gear alternate release
approved the incorporation by reference system could prevent the landing gear from
5680; Internet https://
www.myboeingfleet.com.
of a certain publication listed in this AD extending in the case of a failure of the
(4) You may view this referenced service as of June 4, 2015. normal landing gear extension system.
information at the FAA, Transport Airplane ADDRESSES: You may examine the AD This [Canadian] AD mandates the
Directorate, 1601 Lind Avenue SW., Renton, docket on the Internet at http:// incorporation of a new maintenance task to
WA. For information on the availability of ensure operation of the landing gear alternate
www.regulations.gov/
this material at the FAA, call 425–227–1221. extension system.
#!docketDetail;D=FAA-2015-0074 or in
(5) You may view this service information person at the Docket Management You may examine the MCAI in the
that is incorporated by reference at the AD docket on the Internet at http://
Facility, U.S. Department of
National Archives and Records www.regulations.gov/
Administration (NARA). For information on Transportation, Docket Operations, M–
30, West Building Ground Floor, Room #!documentDetail;D=FAA-2015-0074-
the availability of this material at NARA, call
202–741–6030, or go to: http:// W12–140, 1200 New Jersey Avenue SE., 0003.
www.archives.gov/federal-register/cfr/ibr- Washington, DC. Comments
locations.html. For service information identified in
this AD, contact Bombardier, Inc., 400 We gave the public the opportunity to
Issued in Renton, Washington, on April 13, participate in developing this AD. We
2015. Côte-Vertu Road West, Dorval, Québec
H4S 1Y9, Canada; telephone 514–855– received no comments on the NPRM (80
Michael Kaszycki, FR 3498, January 23, 2015) or on the
5000; fax 514–855–7401; email thd.crj@
Acting Manager, Transport Airplane determination of the cost to the public.
Directorate, Aircraft Certification Service. aero.bombardier.com; Internet http://
www.bombardier.com. You may view Conclusion
[FR Doc. 2015–09805 Filed 4–29–15; 8:45 am]
this referenced service information at
BILLING CODE 4910–13–P We reviewed the relevant data and
the FAA, Transport Airplane
determined that air safety and the
Directorate, 1601 Lind Avenue SW.,
public interest require adopting this AD
DEPARTMENT OF TRANSPORTATION Renton, WA. For information on the
as proposed except for minor editorial
availability of this material at the FAA,
changes. We have determined that these
Federal Aviation Administration call 425–227–1221. It is also available
minor changes:
on the Internet at http:// • Are consistent with the intent that
14 CFR Part 39 www.regulations.gov by searching for was proposed in the NPRM (80 FR 3498,
and locating Docket No. FAA–2015– January 23, 2015) for correcting the
[Docket No. FAA–2015–0074; Directorate 0074.
Identifier 2014–NM–138–AD; Amendment unsafe condition; and
39–18147; AD 2015–09–02] FOR FURTHER INFORMATION CONTACT: • Do not add any additional burden
Cesar Gomez, Aerospace Engineer, upon the public than was already
RIN 2120–AA64
Airframe and Mechanical Systems proposed in the NPRM (80 FR 3498,
Airworthiness Directives; Bombardier, Branch, ANE–171, FAA, New York January 23, 2015).
Inc. Airplanes Aircraft Certification Office, 1600
Related Service Information Under 1
Stewart Avenue, Suite 410, Westbury,
AGENCY: Federal Aviation CFR Part 51
NY 11590; telephone 516–228–7318; fax
Administration (FAA), Department of 516–794–5531. Bombardier, Inc. has issued
Transportation (DOT). SUPPLEMENTARY INFORMATION: Temporary Revision (TR) ALI–0472,
ACTION: Final rule. dated February 27, 2014, to Section 1–
Discussion 32 of Part 2, Bombardier Airworthiness
SUMMARY: We are adopting a new We issued a notice of proposed Limitations, of the CRJ Series Regional
airworthiness directive (AD) for certain rulemaking (NPRM) to amend 14 CFR Jet Maintenance Requirements Manual,
Bombardier, Inc. Model CL–600–2E25 part 39 by adding an AD that would CSP B–053. This service information
(Regional Jet Series 1000) airplanes. apply to certain Bombardier, Inc. Model describes a maintenance task for an
This AD was prompted by a CL–600–2E25 (Regional Jet Series 1000) operational check of the electro-
determination that without an effective airplanes. The NPRM published in the mechanical actuator and release
maintenance task to maintain the Federal Register on January 23, 2015 mechanism of the alternate extension
airplane’s inherent level of safety, there (80 FR 3498). system for the nose landing gear and
is a potential that a dormant failure of Transport Canada Civil Aviation main landing gear. The actions
rmajette on DSK2VPTVN1PROD with RULES
the alternate release system of the (TCCA), which is the aviation authority described in this service information are
landing gear could occur. This AD for Canada, has issued Canadian intended to correct the unsafe condition
requires revising the maintenance or Airworthiness Directive CF–2014–16, identified in the MCAI. This service
inspection program, as applicable, to dated June 11, 2014 (referred to after information is reasonably available at
incorporate a maintenance task for an this as the Mandatory Continuing http://www.regulations.gov by searching
operational check of the electro- Airworthiness Information, or ‘‘the for and locating Docket No. FAA–2015–
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Document Created: 2018-02-21 10:15:16
Document Modified: 2018-02-21 10:15:16
| 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 4, 2015. | |
| Contact | Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 24195 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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