87412 Federal Register / Vol. 81, No. 233 / Monday, December 5, 2016 / Rules and Regulations 

electronic data submission requirement; 

and (5) this rule provides a 60-day 

comment period, and any comments 

received will be considered prior to 

finalization of this rule. 

List of Subjects 

7 CFR Part 944 

Avocados, Food grades and standards, 

Grapefruit, Grapes, Imports, Kiwifruit, 

Olives, Oranges. 

7 CFR Part 980 

Food grades and standards, Imports, 

Marketing agreements, Onions, Potatoes, 

Tomatoes. 

7 CFR Part 999 

Dates, Filberts, Food grades and 

standards, Imports, Nuts, Pistachios, 

Prunes, Raisins, Reporting and 

recordkeeping requirements, Walnuts. 

For the reasons set forth in the 

preamble, 7 CFR parts 944, 980, and 999 

are amended as follows: 

■ 1. The authority citation for 7 CFR 

parts 944, 980, and 999 continues to 

read as follows: 

Authority: 7 U.S.C. 601–674. 

PART 944—FRUITS; IMPORT 

REGULATIONS 

■ 2. Revise § 944.401 paragraph (e) to 

read as follows: 

§ 944.401 Olive Regulation 1. 

* * * * * 

(e) Inspection shall be performed by 

USDA inspectors in accordance with 

said regulations governing the 

inspection and certification of processed 

fruits and vegetables and related 

products (part 52 of this title). The cost 

of each such inspection and related 

certification shall be borne by the 

applicant therefore. Applicants shall 

provide USDA inspectors with the entry 

number and such other identifying 

information for each lot as the inspector 

may request. 

* * * * * 

■ 3. Amend § 980.212 as follows: 

■ a. Revise paragraph (b) introductory 

text; and 

■ b. Remove and reserve paragraphs 

(b)(2) and (3). 

§ 980.212 Import regulations; tomatoes. 

* * * * * 

(b) Grade, size, quality and maturity 

requirements. On and after the effective 

date hereof no person may import fresh 

tomatoes except pear shaped, cherry, 

hydroponic and greenhouse tomatoes as 

defined herein, unless they are 

inspected and meet the following 

requirements: 

* * * * * 

■ 4. In § 980.501, revise the first 

sentence of paragraph (a) introductory 

text and paragraph (a)(4), and add 

paragraph (a)(5) to read as follows: 

§ 980.501 Safeguard procedures for 

potatoes, onions, and tomatoes exempt 

from grade, size, quality and maturity 

requirements. 

(a) Each person who imports or 

receives any of the commodities listed 

in paragraphs (a)(1) through (5) of this 

section shall file (electronically or 

paper) an ‘‘Importer’s Exempt 

Commodity Form’’ (FV–6) with the 

Marketing Order and Agreement 

Division, Specialty Crops Program, 

AMS, USDA. * * * 

(4) Pearl onions; or 

(5) Tomatoes to be used in 

noncommercial outlets for experimental 

purposes. 

* * * * * 

PART 999—SPECIALTY CROPS; 

IMPORT REGULATIONS 

■ 5. Amend § 999.1 as follows: 

■ a. Revise paragraph (c)(1); 

■ b. Remove paragraph (e); and 

■ c. Redesignate paragraphs (f) through 

(i) as (e) through (h), respectively. 

§ 999.1 Regulations governing the 

importation of dates. 

* * * * * 

(c) Inspection and certification 

requirements—(1) Inspection. 

Inspection shall be performed by USDA 

inspectors in accordance with the 

Regulations Governing the Inspection 

and Certification of Processed Fruits 

and Vegetables and Related Products 

(part 52 of this title). The cost of each 

such inspection and related certification 

shall be borne by the applicant. 

Applicants shall provide USDA 

inspectors with the entry number and 

such other identifying information for 

each lot as the inspector may request. 

* * * * * 

■ 6. Amend § 999.600 as follows: 

■ a. Remove paragraph (d)(1); and 

■ b. Redesignate paragraphs (d)(2) and 

(3) as (d)(1) and (2), respectively, and 

revise the newly designated paragraph 

(d)(1). 

§ 999.600 Regulation governing the 

importation of pistachios. 

* * * * * 

(d) Sampling. (1) All sampling for 

aflatoxin testing shall be performed by 

USDA-authorized inspectors in 

accordance with USDA rules and 

regulations governing the inspection 

and certification of fresh fruits, 

vegetables, and other products (7 CFR 

part 51). The cost of each such sampling 

and related certification shall be borne 

by the importer. Whenever pistachios 

are offered for sampling and testing, the 

importer shall furnish any labor and pay 

any costs incurred for storing, moving, 

and opening containers as may be 

necessary for proper sampling and 

testing. The importer shall furnish the 

USDA inspector with the customs entry 

number and such other identifying 

information for each lot as he or she 

may request. Importers may make 

arrangements for required sampling by 

contacting the Inspection Service office 

closest to where the pistachios will be 

made available for sampling. For 

questions regarding sampling, a list of 

Federal or Federal-State Inspection 

Program offices, or for further 

assistance, importers may contact: 

Specialty Crops Inspection Division, 

Specialty Crops Program, AMS, USDA, 

1400 Independence Avenue SW., Room 

1536–S, Washington, DC 20250; 

Telephone: (202) 720–5870; Fax: (202) 

720–0393. 

* * * * * 

Dated: November 29, 2016. 

Elanor Starmer, 

Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2016–29022 Filed 12–2–16; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0215; Directorate 

Identifier 2012–NM–132–AD; Amendment 

39–18665; AD 2016–19–16] 

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 707–300, 

707–300B, and 707–300C series 

airplanes; and certain Model 727C, 727– 

100C, and 727–200F series airplanes. 

This AD was prompted by a report 

indicating that a cam latch on the main 

cargo door (MCD) broke during flight. 

This AD requires various inspections 

and related investigative and corrective 

actions, if necessary. We are issuing this 

AD to address the unsafe condition on 

these products. 

DATES: This AD is effective January 9, 

2017. 


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The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of January 9, 2017. 

ADDRESSES: For service information 

identified in this final rule, 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–2013– 

0215. 

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–2013– 

0215; 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: 

Patrick Farina, Aerospace Engineer, 

Cabin Safety Branch, ANM–150L, FAA, 

Los Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5344; fax: 562–627–5210; 

email: patrick.farina@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain The Boeing Company 

Model 707–300, 707–300B, and 707– 

300C series airplanes; and certain Model 

727C, 727–100C, and 727–200F series 

airplanes. The NPRM published in the 

Federal Register on March 28, 2013 (78 

FR 18922) (‘‘the NPRM’’). The NPRM 

was prompted by a report indicating 

that a cam latch on the MCD broke 

during flight. The NPRM proposed to 

require performing repetitive 

inspections of the MCD cam latches; 

replacing cam latches, certain bolts, and 

door hinge fittings; performing related 

investigative and corrective actions, if 

necessary; and rigging the MCD. We are 

issuing this AD to detect and correct 

discrepancies of the cam latches, latch 

pins, and latch pin cross bolts, which 

could reduce the structural integrity of 

the MCD, and result in potential loss of 

the cargo door and rapid decompression 

of the airplane. 

Actions Since the NPRM Was Issued 

Since we issued the NPRM, we have 

reviewed Boeing 707 Alert Service 

Bulletin A3536, Revision 1, dated 

September 16, 2015 (for Model 707–300, 

707–300B, and 707–300C series 

airplanes); and Boeing Alert Service 

Bulletin 727–52A0150, Revision 1, 

dated November 5, 2015 (for Model 

727C, 727–100C, and 727–200F series 

airplanes). (We referred to Boeing 707 

Alert Service Bulletin A3536, dated 

February 6, 2012; and Boeing Alert 

Service Bulletin 727–52A0150, dated 

January 30, 2012; as the appropriate 

sources of service information for 

accomplishing the actions specified in 

the NPRM.) 

Boeing 707 Alert Service Bulletin 

A3536, Revision 1, dated September 16, 

2015; and Boeing Alert Service Bulletin 

727–52A0150, Revision 1, dated 

November 5, 2015; clarify the inspection 

conditions and the corrective actions for 

certain conditions. Certain inspections 

of the cam latches and latch pins were 

changed from detailed inspections to 

general visual inspections. Also, a 

detailed inspection of mating parts and 

immediately adjacent cam latches and 

latch pins for any cracks or any gouges 

in critical areas was added to certain 

corrective actions specified in the 

service information. 

Also, the corrective actions for latch 

pin extensions that are between 0.84 

and 0.89 inch or between 0.91 and 0.94 

inch were changed. Boeing 707 Alert 

Service Bulletin A3536, Revision 1, 

dated September 16, 2015; and Boeing 

Alert Service Bulletin 727–52A0150, 

Revision 1, dated November 5, 2015; 

specify replacement of any discrepant 

latch pin and a detailed inspection of 

the mating cam latch for any cracks or 

gouges in lieu of the repetitive detailed 

inspections described in Boeing 707 

Alert Service Bulletin A3536, dated 

February 6, 2012; and Boeing Alert 

Service Bulletin 727–52A0150, dated 

January 30, 2012. 

Explanation of Certain Changes to This 

AD 

In light of the issuance of the revised 

service information discussed 

previously, we have revised paragraphs 

(c), (g), and (h) of this AD to refer to 

Boeing 707 Alert Service Bulletin 

A3536, Revision 1, dated September 16, 

2015; and Boeing Alert Service Bulletin 

727–52A0150, Revision 1, dated 

November 5, 2015. We have also added 

new paragraph (l) of this AD to give 

credit for doing actions before the 

effective date of this AD using Boeing 

707 Alert Service Bulletin A3536, dated 

February 6, 2012; and Boeing Alert 

Service Bulletin 727–52A0150, dated 

January 30, 2012. In addition, we have 

removed the Optional Terminating 

Action, which was paragraph (m) in the 

proposed AD, and moved that 

information into paragraph (g)(2) of this 

AD to align with the revised service 

information. We have redesignated 

subsequent paragraphs accordingly. 

In addition, since certain inspections 

and conditions were revised in Boeing 

707 Alert Service Bulletin A3536, 

Revision 1, dated September 16, 2015; 

and Boeing Alert Service Bulletin 727– 

52A0150, Revision 1, dated November 

5, 2015; we have revised the description 

of the actions required by this AD to 

correspond with the terminology used 

in Boeing 707 Alert Service Bulletin 

A3536, Revision 1, dated September 16, 

2015; and Boeing Alert Service Bulletin 

727–52A0150, Revision 1, dated 

November 5, 2015. As a result, certain 

paragraphs in the proposed AD have 

been rearranged, and the corresponding 

paragraph identifiers have been 

redesignated in this AD, as listed in the 

following table: 

REVISED PARAGRAPH IDENTIFIERS

Action in the NPRM 

Corresponding 

requirement in this 

AD 

paragraph (g) ............ paragraph (g)(1). 

paragraph (h) ............ paragraph (g)(2). 

paragraph (i) ............. paragraph (h). 

paragraph (j) ............. paragraph (h). 

paragraph (k) ............ paragraph (k). 

paragraph (l) ............. paragraph (i). 

paragraph (m) ........... paragraph (g)(2). 

paragraph (n) ............ paragraph (j). 

We have also revised the Costs of 

Compliance section in this final rule to 

reflect the number of work-hours 

specified in Boeing 707 Alert Service 

Bulletin A3536, Revision 1, dated 

September 16, 2015; and Boeing Alert 

Service Bulletin 727–52A0150, Revision 

1, dated November 5, 2015. We have 

also included the costs for the repetitive 

inspections required before the MCD 

rigging check as well as replacement of 

the alloy cross bolts; these costs were 

inadvertently omitted from the NPRM. 

In addition, we have included the costs 

for the concurrent actions in Boeing 


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707/720 Service Bulletin 3477, Revision 

2, dated April 15, 1993; and Boeing 

Service Bulletin 727–52–0142, Revision 

2, dated April 15, 1993. 

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. 

FedEx Express had no objection to the 

NPRM. 

Request for Clarification of 

Requirements 

Boeing stated that it was difficult to 

align the requirements proposed in 

paragraphs (g), (h), (i), (j) and (l) of the 

proposed AD with the actions described 

in Boeing 707 Alert Service Bulletin 

A3536, dated February 6, 2012; and 

Boeing Alert Service Bulletin 727– 

52A0150, dated January 30, 2012. 

Boeing commented that it is not clear 

which requirements in the proposed AD 

go with which section of table 1 and 

table 2 in paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 727– 

52A0150, dated January 30, 2012. 

Boeing expressed concern that the 

proposed AD does not include all of the 

items in paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 727– 

52A0150, dated January 30, 2012. 

Boeing suggested that the proposed AD 

be rewritten so operators are not 

confused with unclear compliance 

requirements, which might cause 

situations of non-compliance. 

Boeing also requested that paragraphs 

(h)(1), (h)(2), (h)(3)(i), and (h)(3)(ii) of 

the proposed AD be rewritten to 

improve clarity because words were 

omitted that might lead to confusion or 

misinterpretation of the requirements in 

the proposed AD. 

We agree that the description of the 

parts to be inspected and the required 

tasks should be consistent throughout 

this final rule and should match what is 

described in the Boeing service 

information. With the exception of 

paragraph (l)(2) of this AD, we are 

requiring only actions that are described 

in Boeing 707 Alert Service Bulletin 

A3536, Revision 1, dated September 16, 

2015; and Boeing Alert Service Bulletin 

727–52A0150, Revision 1, dated 

November 5, 2015. We have revised 

paragraphs (g), (h), (i), and (j) of this AD 

accordingly. 

For clarity we have moved the 

‘‘Concurrent Actions’’ paragraph of the 

proposed AD (paragraph (l) of the 

proposed AD) before the ‘‘Exceptions to 

Service Information Specifications’’ 

paragraph (paragraph (k) of the 

proposed AD). In this AD, the 

‘‘Concurrent Actions’’ paragraph is 

redesignated as paragraph (i) of this AD. 

Request To Revise Intervals for 

Repetitive Inspections 

The United States Air Force Joint 

STARS (Joint STARS) program stated 

that its concern is that the NPRM 

addresses only airplanes that are 

frequently used to haul cargo. For 

operators that do not haul cargo and 

typically only open the MCD for Ccheck inspections, the general visual 

inspections required every 330 flight 

cycles or 150 days is excessive. This 

commenter stated that these repetitive 

inspections do not fit into the current 

Joint STARS maintenance program and 

would result in airplane downtime and 

additional cost. This commenter noted 

that detailed inspections every 3,000 

flight cycles or 24 months, and high 

frequency eddy current (HFEC) 

inspections every 6,000 flight cycles or 

48 months, would fit into its current 

maintenance schedule and not cause a 

significant impact. 

We agree that the required intervals 

for repetitive inspections may not be 

appropriate for some operators because 

they infrequently use the cargo door. 

However, we disagree with revising the 

intervals for the repetitive inspections 

required by this AD. We need to 

evaluate the requests for different 

inspection intervals on a case-by-case 

basis, based on the operator and its use 

of the MCD. Operators may request a 

change in the intervals for the repetitive 

inspections by following the procedures 

in paragraph (m) of this AD and 

requesting approval of an alternative 

method of compliance. 

We also note that the FAA has limited 

oversight of public aircraft operations 

(PAO). The government entity 

conducting the PAO is responsible for 

oversight of the operations, including 

aircraft airworthiness. 

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 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 AD. 

Related Service Information Under 

1 CFR Part 51 

We reviewed Boeing 707 Alert Service 

Bulletin A3536, Revision 1, dated 

September 16, 2015; and Boeing Alert 

Service Bulletin 727–52A0150, Revision 

1, dated November 5, 2015. This service 

information describes procedures for 

doing a general visual inspection for 

broken or missing cam latches, latch 

pins, and latch pin cross bolts; 

torqueing the cross bolts in the latch 

pins; measuring the extension of the 

latch pins; replacing all alloy steel cross 

bolts through the latch pins with CRES 

cross bolts; doing a general visual 

inspection of all cam latches for lip 

deformation; doing a HFEC or magnetic 

particle inspection of cam latch 1 and 

cam latch 2 for cracks and replacing all 

cracked or broken parts; checking the rig 

of the MCD and re-rigging as applicable; 

and doing related investigative and 

corrective actions. This service 

information also describes procedures 

for doing repetitive inspections for 

certain conditions specified in the 

service information, which terminate 

after the MCD rigging is done as 

specified in this service information. 

This service information also describes 

procedures for doing MCD post-rigging 

inspections and corrective actions. 

These service bulletins are distinct 

because they apply to different airplane 

models. 

We also reviewed Boeing 707/720 

Service Bulletin 3477, Revision 2, dated 

April 15, 1993; and Boeing Service 

Bulletin 727–52–0142, Revision 2, dated 

April 15, 1993. This service information 

describes procedures for doing general a 

general visual inspection of the hinge 

fittings and the cam latches on the MCD, 

and related investigative and corrective 

actions. These service bulletins are 

distinct because they apply to different 

airplane models. 

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 affects 18 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection/torque/measurement ........... 4 work-hours × $85 per hour = $340 .. $0 .......................... $340 ...................... $6,120. 

Repetitive inspections pre-MCD rigging Up to 3 work-hours × $85 per hour = 

$255 per inspection cycle.

$0 .......................... Up to $255 per inspection cycle.Up to $4,590 per 

inspection cycle. 

MCD rigging/adjustment ....................... 48 work-hours × $85 per hour = 

$4,080.

Up to $8,821 1 ...... Up to $12,901 ....... Up to $232,218. 

Replacement of alloy cross bolts ......... 1 work-hour × $85 per hour = $85 ...... $0 .......................... $85 ........................ $1,530. 

Repetitive inspections post-MCD rigging.3 work-hours × $85 = $255 per inspection cycle.$0 .......................... $255 per inspection cycle.$4,590 per inspection cycle. 

Concurrent 2 inspection ........................ 8 work-hours × $85 per hour = $680 .. $0 .......................... $680 ...................... $12,240. 

1Special tooling is available from the airplane manufacturer; $8,821 is the purchase price and $180 per day is the rental rate. 

2The concurrent inspection is required by AD 91–22–04, Amendment 39–8064 (56 FR 55223, October 25, 1991). 

We estimate the following costs to do 

any necessary related investigative 

actions and certain replacements that 

will be required based on the results of 

the inspections. We have no way of 

determining the number of aircraft that 

might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Related investigative actions ..................................... Up to 3 work-hours × $85 per hour = $255 ............. $0 Up to $255. 

Replacement of broken/missing parts ....................... 1 work-hour × $85 per hour = $85 per latch/pin ..... $0 $85 per latch/pin. 

Concurrent replacement 1 .......................................... 26 work-hours × $85 = $2,210 ................................ $15,324 $17,534. 

1The concurrent replacement of parts is required by AD 91–22–04, Amendment 39–8064 (56 FR 55223, October 25, 1991). 

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 

■ 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): 

2016–19–16 The Boeing Company: 

Amendment 39–18665; Docket No. 

FAA–2013–0215; Directorate Identifier 

2012–NM–132–AD. 

(a) Effective Date 

This AD is effective January 9, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

The Boeing Company airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model 707–300, 707–300B, and 707– 

300C series airplanes, as identified in Boeing 

707 Alert Service Bulletin A3536, Revision 1, 

dated September 16, 2015. 

(2) Model 727C, 727–100C, and 727–200F 

series airplanes, as identified in Boeing Alert 

Service Bulletin 727–52A0150, Revision 1, 

dated November 5, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by a report that a 

cam latch on the main cargo door (MCD) 

broke during flight. We are issuing this AD 

to detect and correct discrepancies of the cam 

latches, latch pins, and latch pin cross bolts. 

Such discrepancies could reduce the 

structural integrity of the MCD, and result in 

potential loss of the cargo door and rapid 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


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(g) MCD Pre-Rig Inspections, Bolt Torque, 

Latch Pin Measurement, Cross Bolt 

Replacement, and Related Investigative and 

Corrective Actions 

(1) Except as provided by paragraph (k)(l) 

of this AD, at the applicable times specified 

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

of Boeing 707 Alert Service Bulletin A3536, 

Revision 1, dated September 16, 2015 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, Revision 1, dated 

November 5, 2015 (for Model 727C, 727– 

100C, and 727–200F series airplanes): Do the 

actions specified in paragraphs (g)(1)(i) 

through (g)(1)(iv) of this AD in accordance 

with the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3536, 

Revision 1, dated September 16, 2015 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, Revision 1, dated 

November 5, 2015 (for Model 727C, 727– 

100C, and 727–200F series airplanes). 

(i) A general visual inspection of the MCD 

for broken or missing cam latches, latch pins, 

and latch pin cross bolts. 

(ii) Torque the cross bolts in the latch pins. 

(iii) Measure the extension of the latch 

pins. 

(iv) Perform a general visual inspection of 

all cam latches for lip deformation. 

(2) Except as required by paragraph (k)(2) 

of this AD, after accomplishing the actions 

specified in paragraphs (g)(1)(i) through 

(g)(1)(iv) of this AD: Do all applicable related 

investigative and corrective actions, replace 

all alloy steel cross bolts through the latch 

pins with corrosion resistant steel (CRES) 

cross bolts, repeat the applicable inspections, 

and do the check of the MCD rig and the 

latch mechanism adjustment test, at the 

applicable times and intervals specified in 

table 1 of paragraph 1.E., ‘‘Compliance,’’ and 

in accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3536, Revision 1, dated September 

16, 2015 (for Model 707–300, 707–300B, and 

707–300C series airplanes); or Boeing Alert 

Service Bulletin 727–52A0150, Revision 1, 

dated November 5, 2015 (for Model 727C, 

727–100C, and 727–200F series airplanes). 

Accomplishment of the check of the MCD rig 

terminates the repetitive inspections required 

by this paragraph. 

(h) MCD Post-Rigging Inspections and 

Corrective Actions 

(1) Except as required by paragraph (k)(2) 

of this AD: At the applicable times specified 

in table 2 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin Boeing 707 

Alert Service Bulletin A3536, Revision 1, 

dated September 16, 2015 (for Model 707– 

300, 707–300B, and 707–300C series 

airplanes); or Boeing Alert Service Bulletin 

727–52A0150, Revision 1, dated November 5, 

2015 (for Model 727C, 727–100C, and 727– 

200F series airplanes): Do general visual 

inspections for any broken or missing cam 

latches, latch pins, and latch pin cross bolts; 

a detailed inspection of the cam latches and 

latch pins for any cracks, or any gouges in 

critical areas; and an HFEC or magnetic 

particle inspection of cam latch 1 and cam 

latch 2 for cracks in critical areas; and do all 

applicable corrective actions; in accordance 

with the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3536, 

Revision 1, dated September 16, 2015 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, Revision 1, dated 

November 5, 2015 (for Model 727C, 727– 

100C, and 727–200F series airplanes). Do all 

applicable corrective actions before further 

flight. 

(2) Repeat the inspections required by 

paragraph (h)(1) of this AD at the applicable 

times specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing 707 Alert Service 

Bulletin A3536, Revision 1, dated September 

16, 2015 (for Model 707–300, 707–300B, and 

707–300C series airplanes); or Boeing Alert 

Service Bulletin 727–52A0150, Revision 1, 

dated November 5, 2015 (for Model 727C, 

727–100C, and 727–200F series airplanes). 

(i) Concurrent Actions 

(1) For airplanes identified in Boeing 707 

Alert Service Bulletin A3536, Revision 1, 

dated September 16, 2015: Before or 

concurrently with accomplishment of the 

general visual inspections specified in 

paragraphs (g)(1)(i) and (g)(1)(iv) of this AD, 

do a general visual inspection of the hinge 

fittings and the cam latches on the MCD, and 

perform related investigative and corrective 

actions as applicable, in accordance with the 

Accomplishment Instructions of Boeing 707/ 

720 Service Bulletin 3477, Revision 2, dated 

April 15, 1993. 

(2) For airplanes identified in Boeing Alert 

Service Bulletin 727–52A0150, Revision 1, 

dated November 5, 2015: Before or 

concurrently with accomplishment of the 

general visual inspections specified in 

paragraphs (g)(1)(i) and (g)(1)(iv) of this AD, 

do a general visual inspection of the hinge 

fittings and the cam latches on the MCD, and 

perform related investigative and corrective 

actions as applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–52–0142, Revision 2, 

dated April 15, 1993. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an alloy steel bolt as a 

cross bolt through any latch pin fitting 

assembly in the lower sill of the MCD on any 

airplane. 

(k) Exceptions to Service Information 

Specifications 

The following exceptions apply to this AD. 

(1) Where Boeing 707 Alert Service 

Bulletin A3536, Revision 1, dated September 

16, 2015 (for Model 707–300, 707–300B, and 

707–300C series airplanes); or Boeing Alert 

Service Bulletin 727–52A0150, Revision 1, 

dated November 5, 2015 (for Model 727C, 

727–100C, and 727–200F series airplanes); 

specifies a compliance time relative to the 

issue date of that service bulletin, this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing 707 Alert Service 

Bulletin A3536, Revision 1, dated September 

16, 2015 (for Model 707–300, 707–300B, and 

707–300C series airplanes); or Boeing Alert 

Service Bulletin 727–52A0150, Revision 1, 

dated November 5, 2015 (for Model 727C, 

727–100C, and 727–200F series airplanes); 

specifies to contact Boeing for appropriate 

action: At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 

Alert Service Bulletin A3536, Revision 1, 

dated September 16, 2015 (for Model 707– 

300, 707–300B, and 707–300C series 

airplanes); or Boeing Alert Service Bulletin 

727–52A0150, Revision 1, dated November 5, 

2015 (for Model 727C, 727–100C, and 727– 

200F series airplanes); repair using a method 

approved in accordance with the procedures 

specified in paragraph (m) of this AD. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

corresponding actions required by 

paragraphs (g) and (h) of this AD, if those 

actions were done before the effective date of 

this AD using Boeing 707 Alert Service 

Bulletin A3536, dated February 6, 2012 (for 

Model 707–300, 707–300B, and 707–300C 

series airplanes); or Boeing Alert Service 

Bulletin 727–52A0150, dated January 30, 

2012 (for Model 727C, 727–100C, and 727– 

200F series airplanes). 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (n)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-AMOCRequests@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, 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. 

(n) Related Information 

(1) For more information about this AD, 

contact Patrick Farina, Aerospace Engineer, 

Cabin Safety Branch, ANM–150L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

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

5344; fax: 562–627–5210; email: 

patrick.farina@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(3) and (o)(4) of this AD. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 


sradovich on DSK3GMQ082PROD with RULES
Federal Register / Vol. 81, No. 233 / Monday, December 5, 2016 / Rules and Regulations 87417 

(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 707 Alert Service Bulletin 

A3536, Revision 1, dated September 16, 

2015. 

(ii) Boeing Alert Service Bulletin 727– 

52A0150, Revision 1, dated November 5, 

2015. 

(iii) Boeing 707/720 Service Bulletin 3477, 

Revision 2, dated April 15, 1993. 

(iv) Boeing Service Bulletin 727–52–0142, 

Revision 2, dated April 15, 1993. 

(3) 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. 

(4) You may view this 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/ibrlocations.html. 

Issued in Renton, Washington, on 

September 14, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–28337 Filed 12–2–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5466; Directorate 

Identifier 2015–NM–183–AD; Amendment 

39–18724; AD 2016–24–07] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 7X 

airplanes. This AD was prompted by 

investigation results that determined 

that a certain thickness of the fuel tank 

panels is insufficient to meet the 

certification requirements. This AD 

requires inspecting the thickness of the 

fuel tank panels, and repair if necessary. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective January 9, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 9, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Dassault Falcon Jet Corporation, 

Teterboro Airport, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http://

www.dassaultfalcon.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–2016– 

5466. 

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– 

5466; 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 street address for 

the Docket Office (telephone 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

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 Dassault Aviation 

Model FALCON 7X airplanes. The 

NPRM published in the Federal 

Register on April 13, 2016 (81 FR 

21770) (‘‘the NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0216, dated October 28, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Dassault 

Aviation Model FALCON 7X airplanes. 

The MCAI states: 

Several rear fuselage tanks of the Falcon 7X 

were assembled on the production line with 

a lateral panel, which had been excessively 

chemically-milled in some areas. 

Investigation results determined that the 

remaining thickness is insufficient to meet 

the certification requirements. Dassault 

Aviation identified the individual aeroplanes 

that are potentially affected by this 

production deficiency. Due to this reduced 

thickness, the risk of damaging and 

puncturing a fuel tank wall panel as a result 

of a high energy lightning strike is increased. 

This condition, if not detected and 

corrected, could lead to loss of electrical 

power and/or other essential functions, 

possibly resulting in reduced control of the 

aeroplane or ignition of a fuel tank. 

To address this potential unsafe condition, 

Dassault Aviation published Service Bulletin 

(SB) 7X–245 to provide inspection and repair 

instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time inspection of 

the fuel tank wall panels and, depending on 

findings, accomplishment of a repair. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

5466. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. 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 AD 

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. 

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 Dassault Service 

Bulletin 7X–245, dated June 8, 2015. 

The service information describes 

procedures for measuring fuel tank 

panel thickness, and repair if necessary. 


sradovich on DSK3GMQ082PROD with RULES