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Federal Register / Vol. 86, No. 204 / Tuesday, October 26, 2021 / Rules and Regulations Low Fuel and Fuel Config Indication Test:
At the applicable time specified in paragraph g12i or ii of this AD.
i For airplanes that did not have any version of AWL No. 28AWL102 in their maintenance or inspection program before the effective date of this AD: Within 750
flight hours since issuance of the original airworthiness certificate or original export certificate of airworthiness; or within 60 days after the effective date of this AD, whichever occurs later.
ii For airplanes not identified in paragraph g12i of this AD: At the latest of the times specified in paragraphs g12iiA through C of this AD.
A Within 750 flight hours since issuance of the original airworthiness certificate or original export certificate of airworthiness.
B Within 750 flight hours after the most recent inspection, if any, was performed as specified in AWL No. 28AWL102.
C Within 750 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 767310295 or Boeing Service Bulletin 767310302, as applicable.
13 For airplanes identified in the applicability for AWL No. 47AWL04, Nitrogen Generation System NGS
Nitrogen-Enriched Air NEA Distribution Ducting: At the applicable time specified in paragraph g13i or ii of this AD.
i For airplanes that did not have any version of AWL No. 47AWL04 in their maintenance or inspection program before the effective date of this AD: Within the applicable interval specified in AWL No. 47
AWL04 since issuance of the original airworthiness certificate or original export certificate of airworthiness, or within 4
months after the effective date of this AD, whichever occurs later.
ii For airplanes not identified in paragraph g13i of this AD: Within the applicable interval specified in AWL No. 47
AWL04 since issuance of the original airworthiness certificate or original export certificate of airworthiness, or within that applicable interval since the most recent inspection, if any, was performed as specified in AWL No. 47AWL04;
whichever occurs later.
14 For airplanes identified in the applicability for AWL No. 47AWL05, Nitrogen Generation System NGSCross Vent Check Valve: At the applicable time specified in paragraph g14i or ii of this AD.
i For airplanes that did not have any version of AWL No. 47AWL05 in their maintenance or inspection program before the effective date of this AD: Within the applicable interval specified in AWL No. 47
AWL05 since issuance of the original airworthiness certificate or original export certificate of airworthiness, or within 4
months after the effective date of this AD, whichever occurs later.
ii For airplanes not identified in paragraph g14i of this AD: Within the applicable interval specified in AWL No. 47
AWL05 since issuance of the original airworthiness certificate or original export certificate of airworthiness, or within that applicable interval since the most recent
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inspection, if any, was performed as specified in AWL No. 47AWL05;
whichever occurs later.
h Additional Acceptable Wire Types and Sleeving As an option, during accomplishment of the actions required by paragraph g of this AD, the changes specified in paragraphs h1 and 2 of this AD are acceptable.
1 Where AWL No. 28AWL09 identifies wire types BMS 1348, BMS 1358, and BMS
1360, the following acceptable wire types and cables can be added to AWL No. 28
AWL09: MILW22759/16, SAE AS22759/
16 formerly M22759/16, MILW22759/32, SAE AS22759/32 formerly M22759/32, MILW22759/34, SAE AS22759/34
formerly M22759/34, MILW22759/41, SAE AS22759/41 formerly M22759/41, MILW22759/86, SAE AS22759/86
formerly M22759/86, MILW22759/87, SAE AS22759/87 formerly M22759/87, MILW22759/92, and SAE AS22759/92
formerly M22759/92; and MILC27500
and NEMA WC 27500 cables that are constructed from these military or SAE
specification wire types, as applicable.
2 Where AWL No. 28AWL09 identifies TFE2X Standard wall for wire sleeving, the following sleeving materials are acceptable:
Roundit 2000NX and Varglas Type HO, HP, or HM, Grade A.
i No Alternative Actions, Intervals, or Critical Design Configuration Control Limitations CDCCLs After the existing maintenance or inspection program has been revised as required by paragraph g of this AD, no alternative actions e.g., inspections, intervals, or CDCCLs may be used unless the actions, intervals, and CDCCLs are approved as an alternative method of compliance AMOC in accordance with the procedures specified in paragraph k of this AD.
j Terminating Action for Certain AD
Requirements Accomplishment of the revision required by paragraph g of this AD terminates the requirements specified in paragraphs j1
through 7 of this AD for that airplane:
1 The revision required by paragraphs g and h of AD 20081101 R1.
2 The revision required by paragraph h of AD 20100610.
3 The revision required by paragraph k of AD 20112505.
4 The revision required by paragraph n of AD 20132502.
5 The revision required by paragraph g of AD 20140809.
6 The revision required by paragraph h of AD 20142002.
7 The revision required by paragraphs i3i and ii of AD 20182013.
k Alternative Methods of Compliance AMOCs 1 The Manager, Seattle ACO Branch, 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 responsible Flight Standards Office, as appropriate. If sending
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information directly to the manager of the certification office, send it to the attention of the person identified in paragraph l1 of this AD. Information may be emailed to: 9ANM-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 responsible Flight Standards 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 Company Organization Designation Authorization ODA that has been authorized by the Manager, Seattle ACO Branch, FAA, 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.
l Related Information For more information about this AD, contact Douglas Mansell, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206231
3875; email: douglas.e.mansell@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. 552a 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 767200/300/300F/400ER
Special Compliance Items/Airworthiness Limitations, D622T001904, dated January 2020.
ii Reserved 3 For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services C&DS, 2600 Westminster Blvd., MC 110SK57, Seal Beach, CA 907405600;
telephone 5627971717; internet https
www.myboeingfleet.com.
4 You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 2062313195.
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, email fr.inspection@nara.gov, or go to:
https www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on September 23, 2021.
Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202123268 Filed 102521; 8:45 am BILLING CODE 491013P

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