Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 43171 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9184; Product 

Identifier 2016–NM–060–AD; Amendment 

39–19032; AD 2017–19–02] 

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 727 

airplanes. This AD was prompted by 

analysis of the cam support assemblies 

of the main cargo door (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 October 19, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 19, 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– 

9184. 

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– 

9184; 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 

727 airplanes. The NPRM published in 

the Federal Register on October 4, 2016 

(81 FR 68373) (‘‘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 AD. 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 Alert 

Service Bulletin 727–52A0151, dated 

February 12, 2016, affects only Boeing 

factory and Boeing converted freighters, 

but the proposed AD extends the 

applicability to all Model 727 airplanes, 

including the ones that have been 

converted by non-Boeing STCs. 

We infer that the commenter is 

requesting that the actions of the service 

information only be required for Model 

727 airplanes identified in the 

Effectivity paragraph of Boeing Alert 

Service Bulletin 727–52A0151, dated 

February 12, 2016. We agree that the 

applicability of the NPRM includes 

some airplanes that do not have the 

identified unsafe condition. The unsafe 

condition does not apply to Model 727 

airplanes that do not have a MCD. 

Therefore, we have revised this AD to 

apply to Model 727 series airplanes 

equipped with a MCD. 

We disagree that the AD applicability 

should be limited to airplanes identified 

in the Effectivity paragraph of Boeing 

Alert Service Bulletin 727–52A0151, 

dated February 12, 2016, which only 

identifies Boeing factory and Boeingconverted freighters. Cam support 

assemblies having an affected part 

number, as specified in paragraphs (g) 

and (h) of this AD, could be installed 

during original aircraft manufacture, or 

during passenger to freighter 

modification. We expect that the actions 

specified in Boeing Alert Service 

Bulletin 727–52A0151, dated February 

12, 2016, can be accomplished on 

airplanes that are not identified in that 

service information. However, if an 

operator cannot accomplish the required 

actions in the service information due to 

the airplane configuration, or prefers to 

use different service information that is 

specific to their design, they can request 

an alternative method of compliance 

(AMOC) in accordance with paragraph 

(j) of this AD. 

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 MCD cam support assemblies 

having part numbers (P/Ns) 69–23588– 

1 and 69–23588–2 as specified in 

Boeing Service Bulletin 727–52A124. 

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 Alert Service Bulletin 

727–52A0151, 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 high frequency eddy 

current inspection 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 inspection 

of the same components as specified in 

the NPRM. Boeing explained that 

cracking initiates at the bottom of the 

lubrication hole inside the cam support 

fitting lug and the cracking is not visible 

until it breaks to the surface of the lug. 

Therefore, the subsurface detection 

capability of the ultrasonic inspection 

provides a more reliable inspection. 


rmajette on DSKBCKNHB2PROD with RULES
43172 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 

We partially agree with Boeing’s 

request to supersede the inspections 

which are required by AD 80–08–10 R1. 

These inspections will overlap with the 

newly mandated repetitive inspections. 

We disagree with the request to revise 

this AD to supersede AD 80–08–10 R1. 

Instead, we have added paragraph (i) to 

this AD to state that completion of the 

initial inspection and all applicable 

replacements required by paragraph (h) 

of this AD terminates all requirements 

of AD 80–08–10 R1, for that airplane 

only. We have redesignated subsequent 

paragraphs accordingly. 

Request To Revise Compliance Time 

Boeing requested that we revise 

paragraph (g)(1) of the proposed AD 

from ‘‘before the accumulation of 18,000 

total flight cycles’’ to ‘‘before the 

accumulation of 18,000 door flight 

cycles. If the door flight cycles are not 

known, use total airplane flight cycles.’’ 

Boeing explained that this change 

would provide relief for operators that 

have converted freighters by delaying 

the required inspection for the MCDs 

that have been in service less than 

18,000 total door flight cycles, but are 

installed on the airplanes that have 

more than 18,000 total airframe flight 

cycles. 

We agree with Boeing’s request. For 

the airplanes that have been converted 

to freighters, the compliance time for 

the initial inspection should be based 

on the number of cycles that the cam 

support assembly has been in service. 

We have revised paragraph (g)(1) of this 

AD accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule 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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 727–52A0151, dated February 

12, 2016. This service information 

describes procedures for an ultrasonic 

inspection of the cam support 

assemblies of the MCD for cracking, and 

replacement if necessary. 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. 

Costs of Compliance 

We estimate that this AD will affect 

45 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 

Inspection ......... 6 work-hours × $85 per hour = $510 per inspection 

cycle.

$0 $510 per inspection cycle $22,950 per inspection 

cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement ................................................................. 60 work-hours × $85 per hour = $5,100 ...................... $14,107 $19,207 

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. 

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 transport category 

airplanes to the Director of the System 

Oversight 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, 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. 


rmajette on DSKBCKNHB2PROD with RULES
Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 43173 

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): 

2017–19–02 The Boeing Company: 

Amendment 39–19032; Docket No. 

FAA–2016–9184; Product Identifier 

2016–NM–060–AD. 

(a) Effective Date 

This AD is effective October 19, 2017. 

(b) Affected ADs 

This AD affects AD 80–08–10 R1, 

Amendment 39–3830 (45 FR 46343, July 10, 

1980). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 727, 727C, 727–100, 727–100C, 727– 

200, and 727–200F series airplanes, 

certificated in any category, equipped with a 

main cargo door (MCD). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Unsafe Condition 

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. 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection To Determine Part Numbers 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: 

Inspect the cam support assemblies of the 

MCD to determine whether part number 

(P/N) 69–23588–1, 69–23588–2, 69–23588–5, 

69–23588–6, 69–23588–9, or 69–23588–10 is 

installed. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number(s) of the cam 

support assemblies of the MCD can be 

conclusively determined from that review. 

(1) Before the accumulation of 18,000 total 

flight cycles since installation of the MCD. If 

the flight cycles since installation of the MCD 

are not known, use total airplane flight 

cycles. 

(2) Within 1,771 flight cycles or 27 months 

after the effective date of this AD, whichever 

occurs later. 

(h) Repetitive Inspections of the Cam 

Support Assemblies of the Main Cargo Door 

and Corrective Actions 

If, during any inspection required by 

paragraph (g) of this AD, any cam support 

assembly of the MCD having P/N 69–23588– 

1, 69–23588–2, 69–23588–5, 69–23588–6, 

69–23588–9, or 69–23588–10 is determined 

to be installed: At the later of the times 

specified in paragraphs (g)(1) and (g)(2) of 

this AD, do an ultrasonic inspection to detect 

cracking of the affected cam support 

assemblies of the MCD; and do all applicable 

replacements; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 727–52A0151, dated 

February 12, 2016. Do all applicable 

replacements before further flight. Repeat the 

inspections thereafter at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 727–52A0151, 

dated February 12, 2016. 

(i) Terminating Action for AD 80–08–10 R1, 

Amendment 39–3830 (45 FR 46343, July 10, 

1980) 

Accomplishment of the initial inspection 

and all applicable replacements required by 

paragraph (h) of this AD terminates all 

requirements of AD 80–08–10 R1, 

Amendment 39–3830 (45 FR 46343, July 10, 

1980), for that airplane only. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 local Flight Standards 

District Office, as appropriate. If sending 

information directly to the manager of the 

certification office, send it to the attention of 

the person identified in paragraph (k) of this 

AD. Information may be emailed to: 9-ANMLAACO-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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO Branch, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

For more information about this AD, 

contact Chandra Ramdoss, Aerospace 

Engineer, Airframe Section, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5239; fax: 562–627–5210; email: 

chandraduth.ramdoss@faa.gov. 

(l) 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 727– 

52A0151, dated February 12, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, 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. 

(4) 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. 

(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. 

Issued in Renton, Washington, on August 

31, 2017. 

Dionne Palermo, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2017–19441 Filed 9–13–17; 8:45 am] 

BILLING CODE 4910–13–P 


rmajette on DSKBCKNHB2PROD with RULES