Federal Register / Vol. 82, No. 192 / Thursday, October 5, 2017 / Rules and Regulations 46379 

(f) When an appeal is required. Before 

seeking review by a court of a 

component’s adverse determination, a 

requester generally must first submit a 

timely administrative appeal. 

§ 102.10 Preservation of records. 

Each component shall preserve all 

correspondence pertaining to the 

requests that it receives under this 

subpart, as well as copies of all 

requested records, until disposition or 

destruction is authorized pursuant to 

title 44 of the United States Code or the 

General Records Schedule 14 of the 

National Archives and Records 

Administration. Records shall not be 

disposed of or destroyed while they are 

the subject of a pending request, appeal, 

or lawsuit under the FOIA. 

§ 102.11 Subpoenas. 

(a) The person to whom the subpoena 

is directed must consult with SBA 

counsel in the relevant SBA office, who 

will seek approval for compliance from 

the Associate General Counsel for 

Litigation. Except where the subpoena 

requires the testimony of an employee 

of the Inspector General’s office, or 

records within the possession of the 

Inspector General, the Associate General 

Counsel may delegate the authorization 

for appropriate production of 

documents or testimony to local SBA 

counsel. 

(b) If SBA counsel approves 

compliance with the subpoena, SBA 

will comply. 

(c) If SBA counsel disapproves 

compliance with the subpoena, SBA 

will not comply, and will base such 

noncompliance on an appropriate legal 

basis such as privilege or a statute. 

(d) SBA counsel must provide a copy 

of any subpoena relating to a criminal 

matter to SBA’s Inspector General prior 

to its return date. 

Appendix A to Subpart A of Part 102— 

Records Maintained by SBA 

I. Information Generally Exempt From 

Disclosure 

a. Non-statistical information on pending, 

declined, withdrawn, or canceled 

applications. 

b. Non-statistical information on defaults, 

delinquencies, losses etc. 

c. Loan status, other than charged-off or 

paid-in-full. 

d. Home disaster loan status and interest 

rate. 

e. Financial statements, credit reports, 

business plans, plant lay-outs, marketing 

strategy, advertising plans, fiscal projections, 

pricing information, payroll information, 

private sector experience and contracts, IRS 

forms, purchase information, banking 

information, corporate structure, research 

plans and client list of applicant/recipient. 

f. Portions of: Certificate of Competency 

records, Requests for Size Determinations, 

8(a) Business Development Plans, loan 

applications, SBIC applications, loan officer’s 

reports. 

g. Internal documents not incorporated 

into final Agency action, pending internal 

recommendations on applications for 

assistance, SBA/attorney-client 

communications, pending litigation 

documents and investigatory documents. 

Discretionary disclosure policy must be 

utilized. 

h. Personal history and financial 

statements, tax forms, resumes, all nongovernment career experience, 

communications regarding applicant’s 

character, home addresses and telephone 

numbers, social security numbers, birth dates 

and medical records. Portions of Inspector 

General (IG) reports, audit reports, program 

investigation records and any other records 

which, if released, would interfere with the 

Government’s law enforcement proceedings 

and/or would reveal the identity of a 

confidential source and documents relating 

to pending litigation and investigations. 

Requests for IG documents must be referred 

to the Office of the Inspector General, 

Counsel Division. 

i. Financial information on portfolio 

companies. 

j. Information originating from other 

agencies should be referred to those agencies 

for disclosure determinations. 

II. Information Generally Disclosed 

a. Names and business addresses of 

recipients of approved loans, SBIC licenses, 

Certificates of Competency, lease guarantees, 

surety bond guarantees and requests for 

counseling. 

b. Names of officers, directors, 

stockholders or partners of recipient firms. 

c. Kinds and amounts of loans, loan terms, 

interest rates (except on home disaster loans), 

maturity dates, general purpose, etc. 

d. Statistical data on assistance, loans, 

defaults, contracts, counseling, etc. 

e. Decisions, rulings and records showing 

final Agency actions in specific factual 

situations if identifying details exempt from 

disclosure are first deleted. 

f. Awarded contracts: names, amounts, 

dates, contracting agencies. 

g. Identity of participating banks. 

h. List of 8(a) participants, date of entry, 

FPPT dates and NAICS codes. 

i. OHA opinions and decisions. 

j. Names of SBA employees, grades, titles, 

and duty stations. 

Linda E. McMahon, 

Administrator. 

[FR Doc. 2017–21204 Filed 10–4–17; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0034; Product 

Identifier 2016–NE–32–AD; Amendment 39– 

19063; AD 2017–20–06] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. 

(Honeywell) AS907–1–1A turbofan 

engines. This AD was prompted by 

reports of loss of power due to failure 

of the second stage low-pressure turbine 

(LPT2) blade. This AD requires a onetime inspection of the LPT2 blades and, 

if the blades fail the inspection, the 

replacement of the blades with a part 

eligible for installation. We are issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective November 9, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 9, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Honeywell International Inc., 111 S 34th 

Street, Phoenix, AZ 85034–2802; phone: 

800–601–3099; Internet: https://

myaerospace.honeywell.com/wps/ 

portal. You may view this service 

information at the FAA, Engine and 

Propeller Standards Branch, 1200 

District Avenue, Burlington, MA 01803. 

For information on the availability of 

this material at the FAA, call (781) 238– 

7125. It is also available on the internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2017–0034. 

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–2017– 

0034; 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 final rule, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 


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46380 Federal Register / Vol. 82, No. 192 / Thursday, October 5, 2017 / Rules and Regulations 

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: 

Joseph Costa, Aerospace Engineer, Los 

Angeles ACO Branch, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562– 

627–5210; email: joseph.costa@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 Honeywell 

International Inc. (Honeywell) AS907– 

1–1A turbofan engines. The NPRM 

published in the Federal Register on 

June 20, 2017 (82 FR 28028). The NPRM 

was prompted by reports of loss of 

power due to failure of the second stage 

LPT2 blade from high-cycle fatigue in 

the blade’s dovetail region. The NPRM 

proposed to require a one-time 

inspection of the LPT2 blades and, if the 

blades fail the inspection, the 

replacement of the blades with a part 

eligible for installation. We are issuing 

this AD to prevent failure of the LPT2 

blades, failure of one or more engines, 

and loss of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We received no comments on the NPRM 

or on the determination of the cost to 

the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed except for minor 

editorial changes. We have determined 

that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Honeywell Service 

Bulletin (SB) AS907–72–9067, Revision 

1, dated March 20, 2017. This SB 

describes procedures for inspecting the 

LPT2 blades. 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. 

Other Related Service Information 

We reviewed Honeywell SB AS907– 

72–9067, Revision 0, dated December 

12, 2016, which also describes 

procedures for inspecting the LPT2 

blades. We also reviewed the Honeywell 

Light Maintenance Manual, AS907–1– 

1A, 72–00–00, Section 72–05–12, dated 

May 25, 2016, and Section 72–55–03, 

dated September 27, 2011, which 

provide additional guidance for 

performing borescope inspections. 

Costs of Compliance 

We estimate that this AD affects 40 

engines installed on airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Borescope inspection ...................................... 10 work-hours × $85 per hour = $850 ........... $0 $850 $34,000 

Report results of inspection ............................ 1 work-hour × $85 per hour = $85 ................. 0 85 3,400 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We estimate that 40 engines 

will need this replacement. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of the LPT2 blade set ............................ 50 work-hours × $85 per hour = $4,250 ...................... $50,000 $54,250 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave., SW., Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

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. 


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Federal Register / Vol. 82, No. 192 / Thursday, October 5, 2017 / Rules and Regulations 46381 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to engines, propellers, and 

associated appliances to the Manager, 

Engine and Propeller Standards Branch, 

Policy and Innovation Division. 

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 to the extent that it justifies 

making a regulatory distinction, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2017–20–06 Honeywell International Inc.: 

Amendment 39–19063; Docket No. 

FAA–2017–0034; Product Identifier 

2016–NE–32–AD. 

(a) Effective Date 

This AD is effective November 9, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Honeywell 

International Inc. (Honeywell) AS907–1–1A 

turbofan engines with second stage lowpressure turbine (LPT2) rotor blades, part 

number (P/N) 3035602–1, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by reports of loss 

of power due to failure of the LPT2 blade. We 

are issuing this AD to prevent failure of the 

LPT2 blades, failure of one or more engines, 

and loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For LPT2 rotor blades, P/N 3035602–1 

that have more than 8,000 hours since new 

on the effective date of this AD, perform a 

one-time borescope inspection for wear of the 

Z gap contact area at the blade tip shroud for 

each of the 62 LPT2 rotor blades within 200 

hours time in service after the effective date 

of this AD. 

(2) Use the Accomplishment Instructions, 

Paragraph 3.B.(1), of Honeywell Service 

Bulletin (SB) AS907–72–9067, Revision 1, 

dated March 20, 2017, to do the inspection. 

(3) If the measured wear and/or fretting of 

any Z gap contact area is greater than 0.005 

inch, replace the LPT2 rotor assembly with 

a part eligible for installation before further 

flight. 

(4) Do the following actions within 200 

hours time in service after the effective date 

of this AD: 

(i) Using a borescope make a clear digital 

image of the Z gap contact area at the blade 

tip shroud of the 62 LPT2 rotor blades. 

(ii) Identify the three Z gap contact areas 

with the greatest amount of wear and/or 

fretting. 

(iii) Record the blade position on the LPT2 

rotor assembly and the measured wear of the 

three Z gap contact areas with the greatest 

amount of wear and/or fretting. 

(iv) Send the results to Honeywell at 

engine.reliability@honeywell.com within 30 

days after completing these actions. 

(g) Credit for Previous Actions 

You may take credit for the actions 

required by paragraphs (f)(1) and (4) of this 

AD, if you performed these actions before the 

effective date of this AD using Honeywell SB 

AS907–72–9067, Revision 0, dated December 

12, 2016. 

(h) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

FAA, may 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 Los Angeles ACO 

Branch, send it to the attention of the person 

identified in paragraph (j) of this AD. 

(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. 

(j) Related Information 

For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles ACO Branch, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

5210; email: joseph.costa@faa.gov. 

(k) 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) Honeywell Service Bulletin AS907–72– 

9067, Revision 1, dated March 20, 2017. 

(ii) Reserved. 

(3) For Honeywell service information 

identified in this AD, contact Honeywell 

International Inc., 111 S 34th Street, Phoenix, 

AZ 85034–2802; phone: 800–601–3099; 

Internet: https://myaerospace.

honeywell.com/wps/portal. 

(4) You may view this service information 

at FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(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/ibrlocations.html. 


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46382 Federal Register / Vol. 82, No. 192 / Thursday, October 5, 2017 / Rules and Regulations 

Issued in Burlington, Massachusetts, on 

September 22, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–21285 Filed 10–4–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9183; Product 

Identifier 2016–NM–059–AD; Amendment 

39–19029; AD 2017–18–20] 

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 The 

Boeing Company Model 707 airplanes 

equipped with a main cargo door 

(MCD). This AD was prompted by 

analysis of the cam support assemblies 

of the MCD that indicated the repetitive 

high frequency eddy current (HFEC) 

inspections required by the existing 

maintenance program are not adequate 

to detect cracks before two adjacent cam 

support assemblies of the MCD could 

fail. This AD requires repetitive 

ultrasonic inspections for cracking of 

the cam support assemblies of the MCD, 

and replacement if necessary. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective November 9, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 9, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; Internet 

https://www.myboeingfleet.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 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– 

9183. 

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– 

9183; 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 final rule, 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: 

Chandra Ramdoss, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5239; fax: 562–627– 

5210; email: chandraduth.ramdoss@

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 all The Boeing Company Model 

707 airplanes. The NPRM published in 

the Federal Register on October 4, 2016 

(81 FR 68376) (‘‘the NPRM’’). The 

NPRM was prompted by analysis of the 

cam support assemblies of the MCD that 

indicated the repetitive HFEC 

inspections required by the existing 

maintenance program are not adequate 

to detect cracks before two adjacent cam 

support assemblies of the MCD could 

fail. The NPRM proposed to require 

repetitive ultrasonic inspections for 

cracking of the cam support assemblies 

of the MCD, and replacement if 

necessary. We are issuing this AD to 

detect and correct cracking of the cam 

support assemblies of the MCD. Such 

cracking could result in reduced 

structural integrity of the MCD and 

consequent rapid decompression of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Revise Applicability 

Boeing stated that Boeing 707 Alert 

Service Bulletin A3542, dated February 

12, 2016, affects only Boeing factory and 

Boeing-converted freighters, but the 

proposed AD extends the applicability 

to all Model 707 airplanes, including 

the ones that have been converted by 

non-Boeing supplemental type 

certificates (STCs). 

We infer the commenter is requesting 

that the actions of the service 

information only be required for Model 

707 airplanes identified in the 

Effectivity paragraph of Boeing 707 

Alert Service Bulletin A3542, dated 

February 12, 2016. We agree that the 

applicability of the proposed AD should 

not include Model 707 airplanes that do 

not have an MCD. However, we disagree 

that the AD applicability should be 

limited to the airplanes identified in the 

Effectivity paragraph of Boeing 707 

Alert Service Bulletin A3542, dated 

February 12, 2016, which only identifies 

Boeing factory and Boeing-converted 

freighters. The cam support assemblies 

having the affected part number could 

be installed at original aircraft 

manufacture, or during passenger-tofreighter modification. We expect that 

the actions specified in Boeing 707 Alert 

Service Bulletin A3542, dated February 

12, 2016, can be accomplished on 

airplanes that are not identified in that 

service information. However, if an 

operator with a Model 707 freighter that 

is not a part of Boeing type design 

cannot accomplish the required actions 

in the service information, or prefers to 

use different service information that is 

specific to their design, approval of an 

alternative method of compliance 

(AMOC) can be requested in accordance 

with paragraph (j) of this AD. We 

revised this AD to limit the applicability 

to Model 707 airplanes equipped with 

an MCD. 

Request To Supersede AD 80–08–10 R1, 

Amendment 39–3830 (45 FR 46343, July 

10, 1980) (‘‘AD 80–08–10 R1’’) 

Boeing requested that we revise the 

NPRM to supersede AD 80–08–10 R1. 

Boeing stated that AD 80–08–10 R1 

mandates HFEC inspections of MCD 

cam support assemblies having part 

numbers (P/Ns) 69–23588–1 and 69– 

23588–2, as specified in Boeing Service 

Bulletin 707–A3387. Boeing explained 

that the NPRM is adding cam support 

assemblies having P/Ns 69–23588–1 and 

69–23588–2 to the list in Boeing 707 

Alert Service Bulletin A3542, dated 

February 12, 2016. Boeing asserted that 

the addition of these components to the 

list of affected parts would mean that 

the operators have to perform HFEC 

inspections of cam support assemblies 

having P/Ns 69–23588–1 and 69– 

23588–2, as specified in AD 80–08–10 

R1, and perform ultrasonic inspections 

of the same components, as specified in 

the proposed AD. Boeing explained that 


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