80 FR 8516 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 32 (February 18, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 32 (February 18, 2015)
| Page Range | 8516-8519 | |
| FR Document | 2015-02689 |
[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)] [Rules and Regulations] [Pages 8516-8519] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-02689] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0522; Directorate Identifier 2014-NM-087-AD; Amendment 39-18100; AD 2015-03-04] 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 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by reports of fuselage skin cracks at the lower forward corner of the main entry door (MED) 1 cutout. This AD requires repetitive inspections of the fuselage skin of the MED 1 cutout for cracking, and repair if necessary; and also provides an optional terminating modification, including post-repair or post-modification fuselage skin inspections for cracking, and corrective actions if necessary. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane. DATES: This AD is effective March 25, 2015. [[Page 8517]] The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 25, 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- 0522. 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- 0522; 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: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. The NPRM published in the Federal Register on August 5, 2014 (79 FR 45385). The NPRM was prompted by reports of fuselage skin cracks at the lower forward corner of the MED 1 cutout. The NPRM proposed to require repetitive inspections of the fuselage skin of the MED 1 cutout for cracking, and repair if necessary. The NPRM also provided optional terminating modification, including post-repair or post-modification inspections for cracking of the fuselage skin, and corrective actions if necessary. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 45385, August 5, 2014) and the FAA's response to each comment. Support for the NPRM (79 FR 45385, August 5, 2014) UPS stated that it agrees with the intent of the NPRM (79 FR 45385, August 5, 2014). Request To Withdraw the NPRM (79 FR 45385, August 5, 2014) Mr. Jerry Adams requested that we withdraw the NPRM (79 FR 45385, August 5, 2014). Mr. Adams stated that the manufacturer's analysis and subsequent action referred to in Boeing Alert Service Bulletin 747- 53A2863, dated March 11, 2014, should be sufficient. Mr. Adams stated that the cost of compliance does not include the increased cost of airframes that the customer must pay for, and that will subsequently be passed along to the traveling consumer. Mr. Adams asserted that this AD action would be counterproductive to business and the cost of transportation to the general public. We agree with the comment that the actions described in Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, are sufficient to correct the identified unsafe condition. However, we do not agree with the commenter's request to withdraw the NPRM (79 FR 45385, August 5, 2014). We have identified an unsafe condition that is likely to exist or develop in other products. Therefore, we must issue an airworthiness directive to correct the identified unsafe condition, as required by section 39.5 of the Federal Aviation Regulations (14 CFR 39.5). We accomplish this by mandating specified actions described in Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, by AD action. We have not changed this AD in this regard. We also note that although the commenter stated that the cost of airframes was not included in the NPRM (79 FR 45385, August 5, 2014), this AD does not require replacing airframes. The costs of accomplishing the actions required by this AD, as specified in Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014 (inspection, repair if necessary, and optional modification), are included in the Costs of Compliance section of this AD. Request To Revise the Description of the Location Where Cracking Was Identified Boeing requested that we revise the SUMMARY and Discussion sections of the preamble, and paragraphs (e), (g), and (i) in the proposed AD (79 FR 45385, August 5, 2014) to clarify that the cracking occurs in the fuselage skin, which would match the title of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014. We agree with the commenter's request because this change will help clarify the cracking location. We have revised this AD accordingly. Request To Revise Service Information and Cost Estimate UPS requested that we revise the service information used in this AD. UPS stated that the power panels and other equipment outboard of the main equipment center (MEC) must be removed in order to access the repair or modification area specified in the NPRM (79 FR 45385, August 5, 2014). UPS stated that these removals are currently not included in the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2863, dated March 11, 2014, and will require significantly greater manpower than specified in the NPRM. We disagree with the commenter's request. We have determined it is not appropriate to delay this AD to incorporate revised service information that might be published sometime in the future. Note 10, in the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2863, dated March 11, 2014, states: If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. Therefore, operators are already permitted to alter the way they gain access to the required areas for inspections/repairs/modifications specified in this AD. We have received no definitive data that would enable us to provide cost estimates for the MEC removal. We have not changed this AD in this regard. [[Page 8518]] 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:Are consistent with the intent that was proposed in the NPRM (79 FR 45385, August 5, 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 45385, August 5, 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 747-53A2863, dated March 11, 2014. The service information describes procedures for inspection, repair, and modification at the lower forward corner of the fuselage main entry door 1. This service information is reasonably available; see ADDRESSES for ways to access this service information. Costs of Compliance We estimate that this AD affects 165 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection (per door)............ 11 work-hours x $85 $0 $935 per inspection $154,275 per per hour = $935 per cycle. inspection cycle. inspection cycle. Optional modification (per door). Up to 66 0 Up to $5,610........ Up to $925,650. work[dash]hours x $85 per hour = $5,610. Post-repair or -modification 11 work-hours x $85 0 $935 per inspection $154,275 per inspection (per door). per hour = $935 per cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repair that would be required based on the results of the inspection. We have no way of determining the number of airplanes that might need this repair: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Repair (per door)............... 66 work-hours x $85 $7,380 or $9,360... $12,990 or $14,970. per hour = $5,610. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 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): 2015-03-04 The Boeing Company: Amendment 39-18100 ; Docket No. FAA- 2014-0522; Directorate Identifier 2014-NM-087-AD. (a) Effective Date This AD is effective March 25, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747- 400D, 747-400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747- 53A2863, dated March 11, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. [[Page 8519]] (e) Unsafe Condition This AD was prompted by reports of fuselage skin cracks at the lower forward corner of the main entry door (MED) 1 cutout. We are issuing this AD to detect and correct skin cracking, which can become large and could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions Except as specified in paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014: Do a detailed inspection and a surface high frequency eddy current inspection for cracking of the fuselage skin at the applicable MED 1 cutout, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014. Do all applicable corrective actions before further flight. Repeat the inspections of the applicable MED 1 cutout thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014. Accomplishing the corrective actions required by this paragraph terminates the repetitive inspection requirements of this paragraph. (h) Optional Terminating Action For airplanes on which no crack is found during the initial inspections required by paragraph (g) of this AD: Installing the preventive modification in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, terminates the repetitive inspections required by paragraph (g) of this AD. (i) Post-Repair or Post-Modification Repetitive Inspections and Corrective Actions For airplanes on which the corrective actions required by paragraph (g) of this AD have been done, or airplanes that have installed the preventive modification specified in paragraph (h) of this AD: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, do a detailed inspection for cracking of the fuselage skin at the applicable MED 1 cutout, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, except as specified in paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the fuselage skin at the applicable MED 1 cutout thereafter at the intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014. (j) Exceptions to Service Information (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, 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) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747-53A2863, dated March 11, 2014, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of 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)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov. (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. (l) Related Information For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov. (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 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 747-53A2863, dated March 11, 2014. (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 February 2, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-02689 Filed 2-17-15; 8:45 am] BILLING CODE 4910-13-P
![8516 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations
test to check for bonding between the re-fuel (j) Corrosion Repair Provision (ii) Reserved.
adaptor of the gravity fill and the top skin As of the effective date of this AD, any (3) For service information identified in
panels on the left-hand and right-hand wings, corrosion repair done on an overwing this AD, contact Airbus, Airworthiness
in accordance with the Accomplishment refueling aperture on any airplane must Office—EIAS, 1 Rond Point Maurice
Instructions of Airbus Service Bulletin A320– comply with the repair requirements of Bellonte, 31707 Blagnac Cedex, France;
57–1152, Revision 01, dated December 19, paragraph (g)(2) of this AD. telephone +33 5 61 93 36 96; fax +33 5 61
2013. 93 44 51; email account.airworth-eas@
(1) If the resistance value is 10 milliohms (k) Other FAA AD Provisions airbus.com; Internet http://www.airbus.com.
or less at the left-hand and right-hand wing, The following provisions also apply to this (4) You may view this service information
no further action is required by this AD: at the FAA, Transport Airplane Directorate,
paragraph. (1) Alternative Methods of Compliance 1601 Lind Avenue SW., Renton, WA. For
(2) If the resistance value is greater than 10 (AMOCs): The Manager, International information on the availability of this
milliohms at the left-hand or right-hand Branch, ANM–116, Transport Airplane material at the FAA, call 425–227–1221.
wing, before further flight, do a general visual Directorate, FAA, has the authority to (5) You may view this service information
inspection for corrosion of the component approve AMOCs for this AD, if requested that is incorporated by reference at the
interface and adjacent area, in accordance using the procedures found in 14 CFR 39.19. National Archives and Records
with the Accomplishment Instructions of In accordance with 14 CFR 39.19, send your Administration (NARA). For information on
Airbus Service Bulletin A320–57–1152, request to your principal inspector or local the availability of this material at NARA, call
Revision 01, dated December 19, 2013. If any Flight Standards District Office, as 202–741–6030, or go to: http://
corrosion is found during the inspection, www.archives.gov/federal-register/cfr/ibr-
appropriate. If sending information directly
before further flight, repair the gravity fill locations.html.
to the International Branch, send it to ATTN:
fuel adaptor, in accordance with the Sanjay Ralhan, Aerospace Engineer, Issued in Renton, Washington, on February
Accomplishment Instructions of Airbus International Branch, ANM–116, Transport 4, 2015.
Service Bulletin A320–57–1152, Revision 01, Airplane Directorate, FAA, 1601 Lind
dated December 19, 2013; except where Dionne Palermo,
Avenue SW., Renton, WA 98057–3356; Acting Manager, Transport Airplane
Airbus Service Bulletin A320–57–1152,
telephone 425–227–1405; fax 425–227–1149. Directorate, Aircraft Certification Service.
Revision 01, dated December 19, 2013,
Information may be emailed to: 9-ANM-116-
specifies to contact Airbus, before further [FR Doc. 2015–02697 Filed 2–17–15; 8:45 am]
AMOC-REQUESTS@faa.gov.
flight, repair using a method approved by the BILLING CODE 4910–13–P
(i) Before using any approved AMOC,
Manager, International Branch, ANM–116,
notify your appropriate principal inspector,
Transport Airplane Directorate, FAA; or the
or lacking a principal inspector, the manager
European Aviation Safety Agency (EASA); or DEPARTMENT OF TRANSPORTATION
of the local flight standards district office/
Airbus’s EASA Design Organization
certificate holding district office. The AMOC
Approval (DOA). If approved by the DOA, Federal Aviation Administration
approval letter must specifically reference
the approval must include the DOA-
authorized signature. this AD.
(ii) AMOCs approved previously for AD 14 CFR Part 39
(h) Credit for Previous Actions 2012–09–07, Amendment 39–17042 (77 FR
28238, May 14, 2012), are approved as [Docket No. FAA–2014–0522; Directorate
This paragraph provides credit for the Identifier 2014–NM–087–AD; Amendment
actions specified in paragraph (g) of this AD, AMOCs for the corresponding provisions of
this AD. 39–18100; AD 2015–03–04]
if those actions were performed before the
effective date of this AD using Airbus Service (2) Contacting the Manufacturer: As of the RIN 2120–AA64
Bulletin A320–57–1152, dated June 14, 2010, effective date of this AD, for any requirement
which was incorporated by reference in AD in this AD to obtain corrective actions from Airworthiness Directives; The Boeing
2012–09–07, Amendment 39–17042 (77 FR a manufacturer, the action must be Company Airplanes
28238, May 14, 2012). accomplished using a method approved by
the Manager, International Branch, ANM– AGENCY: Federal Aviation
(i) New Requirement of This AD: 116, Transport Airplane Directorate, FAA; or Administration (FAA), DOT.
Maintenance Check/Electrical Bonding Test EASA; or Airbus’s EASA DOA. If approved
and Corrective Action if Necessary ACTION: Final rule.
by the DOA, the approval must include the
For airplanes other than those identified in DOA-authorized signature. SUMMARY: We are adopting a new
paragraph (g) of this AD: Within 24 months airworthiness directive (AD) for certain
(l) Related Information
after the effective date of this AD, determine The Boeing Company Model 747–100,
whether a corrosion repair has been done on (1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA 747–100B, 747–100B SUD, 747–200B,
an overwing refueling aperture, whereby a
primer coating has been applied on the Airworthiness Directive 2013–0277R1, dated 747–200C, 747–200F, 747–300, 747–
mating surface of the aperture flange. A December 4, 2013, for related information. 400, 747–400D, 747–400F, 747SR, and
review of the airplane maintenance records is This MCAI may be found in the AD docket 747SP series airplanes. This AD was
acceptable to make this determination, on the Internet at prompted by reports of fuselage skin
provided that whether a primer coat was http://www.regulations.gov/#!document cracks at the lower forward corner of the
applied can be conclusively determined from Detail;D=FAA-2014-0484-0002. main entry door (MED) 1 cutout. This
that review. (2) Service information identified in this AD requires repetitive inspections of the
(1) If it is determined that a primer coating AD that is not incorporated by reference in
fuselage skin of the MED 1 cutout for
was applied on the mating surface of the this AD is available at the addresses specified
aperture flange; or if a determination cannot in paragraphs (m)(4) and (m)(5) of this AD. cracking, and repair if necessary; and
be made, or the outcome is inconclusive: also provides an optional terminating
(m) Material Incorporated by Reference modification, including post-repair or
Within 24 months after the effective date of
this AD do the electrical bonding test (1) The Director of the Federal Register post-modification fuselage skin
specified in paragraph (g) of this AD, and approved the incorporation by reference inspections for cracking, and corrective
mstockstill on DSK4VPTVN1PROD with RULES
before further flight, do all applicable actions (IBR) of the service information listed in this actions if necessary. We are issuing this
specified in paragraph (g)(2) of this AD. paragraph under 5 U.S.C. 552(a) and 1 CFR AD to detect and correct skin cracking,
(2) If it is determined that a corrosion part 51.
which can become large and could
repair has not been done, and a primer (2) You must use this service information
coating has not been applied on the mating as applicable to do the actions required by adversely affect the structural integrity
surface of the aperture flange since first entry this AD, unless this AD specifies otherwise. of the airplane.
into service, no further action is required by (i) Airbus Service Bulletin A320–57–1152, DATES: This AD is effective March 25,
this paragraph. Revision 01, dated December 19, 2013. 2015.
VerDate Sep<11>2014 17:46 Feb 17, 2015 Jkt 235001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\18FER1.SGM 18FER1](https://thefederalregister.org/doc/80_FR_8548/page/1.svg)
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Conclusion • Do not add any additional burden 2014. The service information describes
upon the public than was already procedures for inspection, repair, and
We reviewed the relevant data, proposed in the NPRM (79 FR 45385, modification at the lower forward
considered the comments received, and August 5, 2014). corner of the fuselage main entry door
determined that air safety and the We also determined that these 1. This service information is reasonably
public interest require adopting this AD changes will not increase the economic available; see ADDRESSES for ways to
with the changes described previously burden on any operator or increase the access this service information.
and minor editorial changes. We have scope of this AD.
determined that these minor changes: Costs of Compliance
• Are consistent with the intent that Related Service Information Under 1 We estimate that this AD affects 165
was proposed in the NPRM (79 FR CFR Part 51 airplanes of U.S. registry.
45385, August 5, 2014) for correcting We reviewed Boeing Alert Service We estimate the following costs to
the unsafe condition; and Bulletin 747–53A2863, dated March 11, comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection (per door) ............... 11 work-hours × $85 per hour $0 $935 per inspection cycle ....... $154,275 per inspection cycle.
= $935 per inspection cycle.
Optional modification (per Up to 66 work-hours × $85 0 Up to $5,610 ........................... Up to $925,650.
door). per hour = $5,610.
Post-repair or -modification in- 11 work-hours × $85 per hour 0 $935 per inspection cycle ....... $154,275 per inspection cycle.
spection (per door). = $935 per inspection cycle.
We estimate the following costs to do required based on the results of the determining the number of airplanes
any necessary repair that would be inspection. We have no way of that might need this repair:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Repair (per door) .............................. 66 work-hours × $85 per hour = $7,380 or $9,360 .............................. $12,990 or $14,970.
$5,610.
Authority for This Rulemaking distribution of power and PART 39—AIRWORTHINESS
Title 49 of the United States Code responsibilities among the various DIRECTIVES
specifies the FAA’s authority to issue levels of government.
■ 1. The authority citation for part 39
rules on aviation safety. Subtitle I, For the reasons discussed above, I continues to read as follows:
section 106, describes the authority of certify that this AD:
the FAA Administrator. Subtitle VII: Authority: 49 U.S.C. 106(g), 40113, 44701.
(1) Is not a ‘‘significant regulatory
Aviation Programs, describes in more action’’ under Executive Order 12866, § 39.13 [Amended]
detail the scope of the Agency’s
authority. (2) Is not a ‘‘significant rule’’ under ■ 2. The FAA amends § 39.13 by adding
DOT Regulatory Policies and Procedures the following new airworthiness
We are issuing this rulemaking under
(44 FR 11034, February 26, 1979), directive (AD):
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701: (3) Will not affect intrastate aviation 2015–03–04 The Boeing Company:
‘‘General requirements.’’ Under that in Alaska, and Amendment 39–18100 ; Docket No.
FAA–2014–0522; Directorate Identifier
section, Congress charges the FAA with (4) Will not have a significant 2014–NM–087–AD.
promoting safe flight of civil aircraft in economic impact, positive or negative,
air commerce by prescribing regulations (a) Effective Date
on a substantial number of small entities
for practices, methods, and procedures This AD is effective March 25, 2015.
under the criteria of the Regulatory
the Administrator finds necessary for (b) Affected ADs
Flexibility Act.
safety in air commerce. This regulation
is within the scope of that authority None.
List of Subjects in 14 CFR Part 39
because it addresses an unsafe condition (c) Applicability
that is likely to exist or develop on Air transportation, Aircraft, Aviation This AD applies to The Boeing Company
products identified in this rulemaking safety, Incorporation by reference, Model 747–100, 747–100B, 747–100B SUD,
action. Safety. 747–200B, 747–200C, 747–200F, 747–300,
747–400, 747–400D, 747–400F, 747SR, and
mstockstill on DSK4VPTVN1PROD with RULES
Regulatory Findings Adoption of the Amendment 747SP series airplanes, certificated in any
This AD will not have federalism category, as identified in Boeing Alert
Accordingly, under the authority Service Bulletin 747–53A2863, dated March
implications under Executive Order delegated to me by the Administrator, 11, 2014.
13132. This AD will not have a the FAA amends 14 CFR part 39 as
substantial direct effect on the States, on (d) Subject
follows:
the relationship between the national Air Transport Association (ATA) of
government and the States, or on the America Code 53, Fuselage.
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![Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Rules and Regulations 8519
(e) Unsafe Condition (j) Exceptions to Service Information Administration (NARA). For information on
This AD was prompted by reports of (1) Where paragraph 1.E., ‘‘Compliance,’’ of the availability of this material at NARA, call
fuselage skin cracks at the lower forward Boeing Alert Service Bulletin 747–53A2863, 202–741–6030, or go to: http://
corner of the main entry door (MED) 1 dated March 11, 2014, specifies a compliance www.archives.gov/federal-register/cfr/ibr-
time ‘‘after the Original issue date of this locations.html.
cutout. We are issuing this AD to detect and
correct skin cracking, which can become service bulletin,’’ this AD requires
compliance within the specified compliance Issued in Renton, Washington, on February
large and could adversely affect the structural 2, 2015.
integrity of the airplane. time after the effective date of this AD.
(2) If any cracking is found during any Jeffrey E. Duven,
(f) Compliance inspection required by this AD, and Boeing Manager, Transport Airplane Directorate,
Comply with this AD within the Alert Service Bulletin 747–53A2863, dated Aircraft Certification Service.
compliance times specified, unless already March 11, 2014, specifies to contact Boeing [FR Doc. 2015–02689 Filed 2–17–15; 8:45 am]
done. for appropriate action: Before further flight,
BILLING CODE 4910–13–P
repair the cracking using a method approved
(g) Repetitive Inspections and Corrective in accordance with the procedures specified
Actions in paragraph (k) of this AD.
Except as specified in paragraph (j)(1) of (k) Alternative Methods of Compliance DEPARTMENT OF COMMERCE
this AD, at the applicable time specified in (AMOCs)
paragraph 1.E., ‘‘Compliance,’’ of Boeing Bureau of Industry and Security
Alert Service Bulletin 747–53A2863, dated (1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
March 11, 2014: Do a detailed inspection and 15 CFR Parts 730 and 744
authority to approve AMOCs for this AD, if
a surface high frequency eddy current
requested using the procedures found in 14 [Docket No. 150123073–5073–01]
inspection for cracking of the fuselage skin at
CFR 39.19. In accordance with 14 CFR 39.19,
the applicable MED 1 cutout, and do all RIN 0694–AG48
send your request to your principal inspector
applicable corrective actions, in accordance
or local Flight Standards District Office, as
with the Accomplishment Instructions of Updated Statements of Legal Authority
appropriate. If sending information directly
Boeing Alert Service Bulletin 747–53A2863,
to the manager of the ACO, send it to the for the Export Administration
dated March 11, 2014. Do all applicable
attention of the person identified in Regulations To Include Presidential
corrective actions before further flight. paragraph (l)(1) of this AD. Information may
Repeat the inspections of the applicable MED Notice of January 21, 2015
be emailed to: 9-ANM-Seattle-ACO-AMOC-
1 cutout thereafter at the applicable intervals Requests@faa.gov. AGENCY: Bureau of Industry and
specified in paragraph 1.E., ‘‘Compliance,’’ of (2) Before using any approved AMOC,
Boeing Alert Service Bulletin 747–53A2863,
Security, Commerce.
notify your appropriate principal inspector, ACTION: Final rule.
dated March 11, 2014. Accomplishing the or lacking a principal inspector, the manager
corrective actions required by this paragraph of the local flight standards district office/
terminates the repetitive inspection SUMMARY: This rule updates the Code of
certificate holding district office.
requirements of this paragraph. Federal Regulations (CFR) legal
(l) Related Information authority paragraphs in the Export
(h) Optional Terminating Action
For more information about this AD, Administration Regulations (EAR) to
For airplanes on which no crack is found contact Nathan Weigand, Aerospace cite a Presidential notice that extended
during the initial inspections required by Engineer, Airframe Branch, ANM–120S, an emergency declared pursuant to the
paragraph (g) of this AD: Installing the Seattle Aircraft Certification Office (ACO), International Emergency Economic
preventive modification in accordance with FAA, 1601 Lind Avenue SW., Renton, WA
the Accomplishment Instructions of Boeing
Powers Act. This is a procedural rule
98057–3356; phone: 425–917–6428; fax: 425– that only updates authority paragraphs
Alert Service Bulletin 747–53A2863, dated 917–6590; email:
March 11, 2014, terminates the repetitive of the EAR. It does not alter any right,
Nathan.P.Weigand@faa.gov.
inspections required by paragraph (g) of this obligation or prohibition that applies to
AD. (m) Material Incorporated by Reference any person under the EAR.
(i) Post-Repair or Post-Modification (1) The Director of the Federal Register DATES: The rule is effective February 18,
Repetitive Inspections and Corrective approved the incorporation by reference 2015.
Actions (IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR FOR FURTHER INFORMATION CONTACT:
For airplanes on which the corrective part 51. William Arvin, Regulatory Policy
actions required by paragraph (g) of this AD (2) You must use this service information Division, Bureau of Industry and
have been done, or airplanes that have as applicable to do the actions required by Security, Email william.arvin@
installed the preventive modification this AD, unless the AD specifies otherwise. bis.doc.gov, Telephone: (202) 482–2440.
specified in paragraph (h) of this AD: At the (i) Boeing Alert Service Bulletin 747– SUPPLEMENTARY INFORMATION:
applicable time specified in paragraph 1.E., 53A2863, dated March 11, 2014.
‘‘Compliance,’’ of Boeing Alert Service (ii) Reserved. Background
Bulletin 747–53A2863, dated March 11, (3) For Boeing service information
2014, do a detailed inspection for cracking of identified in this AD, contact Boeing The authority for parts 730 and 744 of
the fuselage skin at the applicable MED 1 Commercial Airplanes, Attention: Data & the EAR (15 CFR parts 730 and 744)
cutout, and do all applicable corrective Services Management, P.O. Box 3707, MC rests, in part, on Executive Order 12947
actions, in accordance with the 2H–65, Seattle, WA 98124–2207; telephone of January 23, 1995—Prohibiting
Accomplishment Instructions of Boeing Alert 206–544–5000, extension 1; fax 206–766– Transactions With Respect to Terrorists
Service Bulletin 747–53A2863, dated March 5680; Internet https:// Who Threaten To Disrupt the Middle
11, 2014, except as specified in paragraph www.myboeingfleet.com. East Peace Process (60 FR 5079, 3 CFR,
mstockstill on DSK4VPTVN1PROD with RULES
(j)(2) of this AD. Do all applicable corrective (4) You may view this referenced service 1995 Comp., p. 356) and on annual
actions before further flight. Repeat the information at the FAA, Transport Airplane
inspection of the fuselage skin at the
notices by the President continuing the
Directorate, 1601 Lind Avenue SW., Renton,
applicable MED 1 cutout thereafter at the WA. For information on the availability of emergency declared in that order. This
intervals specified in paragraph 1.E., this material at the FAA, call 425–227–1221. rule updates the authority paragraphs in
‘‘Compliance,’’ of Boeing Alert Service (5) You may view this service information 15 CFR parts 730 and 744 to cite the
Bulletin 747–53A2863, dated March 11, that is incorporated by reference at the Notice of January 21, 2015, 80 FR 3461
2014. National Archives and Records (January 22, 2015), which is the most
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Document Created: 2018-02-16 11:10:23
Document Modified: 2018-02-16 11:10:23
| 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 March 25, 2015. | |
| Contact | Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 8516 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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