Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 52177 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Within 18 months after the effective date 

of this AD: Perform a detailed inspection of 

the uplock springs of the MLG and NLG legs 

and doors for broken and damaged springs, 

in accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (g)(1), 

(g)(2), or (g)(3) of this AD. Repeat the 

inspection thereafter at intervals not to 

exceed 18 months. 

(1) Airbus Service Bulletin A300–32–0465, 

Revision 01, dated April 25, 2013 (for Model 

A300 series airplanes). 

(2) Airbus Service Bulletin A300–32–6111, 

Revision 01, dated April 25, 2013 (for Model 

A300–600 series airplanes). 

(3) Airbus Service Bulletin A310–32–2147, 

Revision 01, dated April 25, 2013 (for Model 

A310 series airplanes). 

(h) Corrective Actions 

The corrective actions required by 

paragraphs (h)(1), (h)(2), and (h)(3) of this AD 

do not constitute terminating actions for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(1) If, during any inspection required by 

paragraph (g) of this AD, one spring on the 

MLG or NLG door uplock is found broken or 

damaged, within 2 months after the 

inspection, replace the affected MLG or NLG 

door uplock, as applicable, with a serviceable 

part, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

(2) If, during any inspection required by 

paragraph (g) of this AD, one spring on the 

MLG or NLG leg uplock is found broken or 

damaged, repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed 50 flight cycles. 

Replacement of any affected leg uplock, as 

required by paragraph (h)(2)(i) or (h)(2)(ii) of 

this AD, as applicable, constitutes 

terminating action for the repetitive 

inspections required by paragraph (h)(2) of 

this AD. 

(i) If, during any inspection required by 

paragraph (h)(2) of this AD, the second free 

fall spring on the MLG or NLG leg uplock is 

found broken or damaged, before further 

flight, replace the affected MLG or NLG leg 

uplock, as applicable, with a serviceable part, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. 

(ii) Within 1,000 flight cycles after doing 

the inspection required by paragraph (g) of 

this AD during which the spring has been 

found broken, replace the affected MLG or 

NLG leg uplock, as applicable, with a 

serviceable part, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

(3) If, during any inspection required by 

paragraph (g) of this AD, two free fall springs 

on the same MLG or NLG leg uplock are 

found broken or damaged, before further 

flight, replace the affected MLG or NLG leg 

uplock, as applicable, with a serviceable part, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

applicable actions required by paragraphs (g) 

and (h) of this AD, if those actions were 

performed before the effective date of this AD 

using the applicable service information 

identified in paragraph (i)(1), (i)(2), or (i)(3) 

of this AD. 

(1) Airbus Service Bulletin A300–32–0465, 

dated July 20, 2012, which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A300–32–6111, 

dated July 20, 2012, which is not 

incorporated by reference in this AD. 

(3) Airbus Service Bulletin A310–32–2147, 

dated July 20, 2012, which is not 

incorporated by reference in this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0150, dated 

July 16, 2013, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0137-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

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

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–32–0465, 

Revision 01, dated April 25, 2013. 

(ii) Airbus Service Bulletin A300–32–6111, 

Revision 01, dated April 25, 2013. 

(iii) Airbus Service Bulletin A310–32– 

2147, Revision 01, dated April 25, 2013. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.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 August 

15, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20259 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0617; Directorate 

Identifier 2014–CE–019–AD; Amendment 

39–17962; AD 2014–17–09 

RIN 2120–AA64 

Airworthiness Directives; Various de 

Havilland Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Harry E. Williams de Havilland Model 

DH 82A airplanes, all Cliff Robertson de 

Havilland Model DH 82A airplanes, and 

all de Havilland Model DH 83 airplanes. 

This AD requires inspecting the aircraft 

maintenance records and/or the 

installed lateral fuselage tie rods and 


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52178 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 

attaching nuts to determine the origin of 

manufacture. This AD also requires 

immediately replacing lateral fuselage 

tie rods and attaching nuts produced by 

a specific manufacturer. This AD was 

prompted by reports of structural failure 

of the attachment of the wing to the 

fuselage that resulted from failed lateral 

fuselage tie rods. We are issuing this AD 

to correct the unsafe condition on these 

products. 

DATES: This AD is effective September 

18, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 18, 2014. 

We must receive comments on this 

AD by October 20, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, for de Havilland DH 82A 

airplanes, contact de Havilland Support 

Ltd., Building 213, Duxford Airfield, 

Cambridge, United Kingdom CB22 4QR, 

telephone: +44 (0) 1223 830090; fax: +44 

(0) 1223 83008; email: info@

dhsupport.com, Internet: http:// 

www.dhsupport.com/moth.php. 

For service information identified in 

this AD, for de Havilland DH 83, contact 

Air Stratus Ltd., Oaksey Park Airfield, 

Oaksey, Malmesbury, Wiltshite, United 

Kingdom SN 16 9SD, telephone: +44 (0) 

1666 575111; no known Internet 

address. 

You may view this referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64016. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0617; 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 (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: For 

airplanes covered under Type 

Certificate Data Sheet (TCDS) A5PC 

(Model de Havilland DH 82A airplanes 

built in Australia): Andrew McAnaul, 

Aerospace Engineer, FAA, Fort Worth 

Airplane Certification Office, ASW–150 

(c/o San Antonio MIDO), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; phone: (210) 308–3365; 

fax: (210) 308–3370; email: 

andrew.mcanaul@faa.gov. 

For airplanes covered under TCDS 

A8EU (Model de Havilland DH 82A 

airplanes built in the United Kingdom): 

Fred Guerin, Aerospace Engineer, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Blvd., Suite 

100, Lakewood, California 90712; phone 

(562) 627–5232; fax: (562) 627–5210; 

email: fred.guerin@faa.gov. 

For airplanes covered under TCDS 2– 

439 (Model de Havilland DH 83 

airplanes built in the United Kingdom): 

Karl Schletzbaum, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; phone: (816) 329–4123; 

fax: (816) 329–4090; email: 

karl.schletzbaum@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report from the 

Australia Transportation Safety Board 

(ASTB) of accident investigation results 

on a de Havilland Model DH 82A 

airplane, which had a wing failure in 

flight. Investigation revealed that both of 

the accident airplane’s fuselage lateral 

tie rods, which join the lower wings to 

the fuselage, were found fractured in 

three of the four threaded sections near 

the join with the left wing. The failed 

lateral fuselage tie rods, part number 

JRA–776–1, were under an Australian 

parts manufacturing approval (PMA) 

and were found to have different 

characteristics than the OEM parts. 

Although the defective PMA parts 

were manufactured in Australia, some 

airplanes of U.S. registry may have the 

PMA parts installed. 

De Havilland Model DH 82A 

airplanes (commonly referred to as Tiger 

Moths) are type certificated under two 

type certificates. TCDS A5PC, currently 

held by Harry E. Williams, is for 

airplanes built in Australia, and TCDS 

A8EU, currently held by Cliff Robertson, 

c/o Gadbois Business Management, is 

for airplanes built in the United 

Kingdom. This type certification 

approval was not by validation, but by 

an acceptance process; as such, the U.S. 

type certificate holders are not the 

manufacturers of the airplanes and the 

original manufacturers (de Havilland 

and its licensees) are not type certificate 

holders. 

De Havilland Support Ltd (DHSL) 

holds the type certificate responsibility 

for de Havilland Model DH 82A 

airplanes (the type design for TCDS 

A8EU) in the United Kingdom. 

DHSL is custodian of the airframe 

design data, manufacturing drawings, 

and repair schemes still in existence for 

de Havilland Model DH 82A Tiger Moth 

series airplanes only. In 2012, DHSL 

entered into a CAA Type Responsibility 

Agreement (TRA) so that the airplane 

remains eligible, if required, for an 

ICAO-compliant Certificate of 

Airworthiness to facilitate training and 

pleasure flying. 

Similarly, Air Stratus Ltd holds the 

type certificate responsibility for de 

Havilland Model DH 83 airplanes (the 

type design for TCDS 2–439) in the 

United Kingdom. 

The process for making mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country mandatory for 

airplanes of U.S. registry is through 

rulemaking. 

This condition, if not corrected, could 

result in structural failure of the 

attachment of the wing to the fuselage. 

We are issuing this AD to correct the 

unsafe condition on these products. 

Relevant Service Information 

We reviewed British Aerospace 

Military Aircraft and Aerostructures 

BAe Aircraft Bulletin for de Havilland 

Moth Aircraft, Document Type and Ref 

No Technical News Sheet CT (Moth) No 

29, Issue 3, dated March 1, 1999, which 

was approved by the Civil Aviation 

Authority (CAA) for the United 

Kingdom to ensure the continued 

airworthiness of these airplanes in the 

United Kingdom. The service 

information describes procedures for 

replacing the lateral tie rods and 

attaching nuts. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 


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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 52179 

AD Requirements 

This AD requires inspecting the 

aircraft maintenance records and/or the 

installed lateral fuselage tie rods and 

attaching nuts to determine if they were 

produced by J & R Aerospace Pty Ltd. 

This AD also requires replacing all 

lateral fuselage tie rods and attaching 

nuts produced by J & R Aerospace Pty 

Ltd with airworthy parts. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because structural failure of the 

attachment of the wing to the fuselage 

could result in loss of control. 

Therefore, we find that notice and 

opportunity for prior public comment 

are impracticable and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2014–0617 and Directorate 

Identifier 2014–CE–019–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 69 

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 

Inspect the aircraft maintenance records and/or the 

lateral fuselage tie rod s and attaching nuts to determine the lateral fuselage tie rods and attaching 

nuts origin of manufacture.

1 work-hour × $85 per 

hour = $85.

Not applicable .................. $85 $5,865 

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 airplanes 

that might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace lateral fuselage tie rods and attaching nuts ................................ 30 work-hours × $85 per hour = 

$2,550.

$825 $3,375 

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): 

2014–17–09 Harry E. Williams, Cliff 

Robertson, and de Havilland Airplanes: 

Amendment 39–17962; Docket No. 


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52180 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations 

FAA–2014–0617; Directorate Identifier 

2019–CE–019–AD. 

(a) Effective Date 

This AD is effective September 18, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Harry E. Williams and 

Cliff Robertson Model de Havilland DH 82A 

airplanes, all serial numbers, and de 

Havilland Model DH 83 airplanes, all serial 

numbers, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 5341, Fuselage, Wing Attach Fittings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

structural failure of the attachment of the 

wing to the fuselage that resulted from failed 

lateral fuselage tie rods. We are issuing this 

AD to correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraphs (g) 

through (j) of this AD, unless already done. 

(g) Restrict Airplane Operation 

(1) As of September 18, 2014 (the effective 

date of this AD), the airplane is restricted to 

non-aerobatic flight until the actions required 

in paragraphs (h)(1) through (i)(1) of this AD 

are done. 

(2) As of September 18, 2014 (the effective 

date of this AD), before further flight, place 

a copy of this AD into the Limitations section 

of the airplane flight manual (AFM). 

(h) Determine Manufacture of Installed 

Lateral Fuselage Tie Rods and Attaching 

Nuts 

Within the next 10 hours time-in-service 

(TIS) after September 18, 2014 (the effective 

date of this AD), review the aircraft 

maintenance records and/or inspect the 

installed lateral fuselage tie rods and 

attaching nuts to determine if the lateral 

fuselage tie rods and attaching nuts were 

produced by J & R Aerospace Pty Ltd., P/N 

JRA–776–1 (for de Havilland Model DH 82A 

airplanes), and P/N JRA–776–3 (for de 

Havilland Model DH 83 airplanes). 

(1) If you are able to positively determine 

that the installed lateral fuselage tie rods and 

attaching nuts are not produced by J & R 

Aerospace Pty Ltd, remove the flight 

restriction required in paragraph (g) of this 

AD, and no further action is required by this 

AD. 

(2) If you are not able to positively 

determine that the installed lateral fuselage 

tie rods and attaching nuts are not produced 

by J & R Aerospace Pty Ltd or if you 

determine that the installed lateral fuselage 

tie rods and attaching nuts are produced by 

J & R Aerospace, before further flight, remove 

and replace the lateral fuselage tie rods and 

attaching nuts as specified in paragraph (i) of 

this AD. 

(i) Remove and Replace Lateral Fuselage Tie 

Rods and Attaching Nuts Produced by J & R 

Aerospace Pty Ltd 

(1) Before further flight after making the 

determination required in paragraph (h)(2) of 

this AD, remove and destroy the installed 

lateral fuselage tie rods and attaching nuts 

and replace the lateral fuselage tie rods and 

attaching nuts. Replace the lateral tie rods 

and attaching nuts following the procedures 

in paragraph 2.C. of the Accomplishment 

Instructions and using the table on Figure 1 

in British Aerospace Military Aircraft and 

Aerostructures BAe Aircraft Bulletin for De 

Havilland Moth Aircraft, Document Type and 

Ref No Technical News Sheet CT (Moth) No 

29, Issue 3, dated March 1, 1999. 

(2) Before further flight after doing the 

replacement required in paragraph (i)(1) of 

this AD, remove the flight restriction 

required in paragraph (g) of this AD. 

(j) Prohibited Installation 

As of September 18, 2014 (the effective 

date of this AD), do not install P/N JRA–776– 

1 or JRA–776–3 lateral fuselage tie rods 

manufactured under Australian part 

manufacture approval (PMA) manufacturer J 

& R Aerospace Pty Ltd. 

(k) Special Flight Permit 

Special flight permits are permitted with 

the following limitations: 

(1) No passengers, 

(2) Day VRF only, 

(3) Straight and level flight, and 

(4) Avoid areas of known turbulence. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager of the Fort Worth 

Airplane Certification Office (ACO), the 

Manager of the Los Angeles Aircraft 

Certification Office (ACO), and the Manager 

of the Standards Office, FAA, have the 

authority to approve AMOCs for their 

respective products covered by 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 applicable FAA office, 

send it to the attention of the person 

identified in paragraph (n). 

(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. 

(m) Related Information 

(1) For more information about this AD for 

airplanes covered under TCDS A5PC (Model 

de Havilland DH 82A airplanes built in 

Australia), contact Andrew McAnaul, 

Aerospace Engineer, FAA, Fort Worth ACO, 

ASW–150 (c/o San Antonio MIDO), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; phone: (210) 308–3365; fax: 

(210) 308–3370; email: andrew.mcanaul@

faa.gov. 

(2) For more information about this AD for 

airplanes covered under TCDS A8EU (Model 

de Havilland DH 82A airplanes built in the 

United Kingdom), contact Fred Guerin, 

Aerospace Engineer, FAA, Los Angeles ACO, 

3960 Paramount Blvd., Suite 100, Lakewood, 

California 90712; phone (562) 627–5232; fax: 

(562) 627–5210; email: fred.guerin@faa.gov. 

(3) For more information about this AD for 

airplanes covered under TCDS 2–439 (Model 

de Havilland DH 83 airplanes built in the 

United Kingdom), contact Karl Schletzbaum, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329– 

4123; fax: (816) 329–4090; email: 

karl.schletzbaum@faa.gov 

(n) 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) British Aerospace Military Aircraft and 

Aerostructures BAe Aircraft Bulletin for De 

Havilland Moth Aircraft, Document Type and 

Ref No Technical News Sheet CT (Moth) No 

29, Issue 3, dated March 1, 1999. 

(ii) Reserved. 

(3) For British Aerospace Military Aircraft 

and Aerostructures BAe Aircraft Bulletin for 

De Havilland Moth Aircraft, Technical New 

Sheet CT (Moth) No 29, Issue 3, dated March 

1, 1999, service information identified in this 

AD, contact: 

(i) For de Havilland DH 82A airplanes: de 

Havilland Support Ltd, Building 213, 

Duxford Airfield, Cambridge, United 

Kingdom CB22 4QR, telephone: +44 (0) 1223 

830090; fax: +44 (0) 1223 83008; email: info@

dhsupport.com, Internet: http://

www.dhsupport.com/moth.php. 

(ii) For de Havilland DH 83 airplanes: Air 

Stratus Ltd., Oaksey Park Airfield, Oaksey, 

Malmesbury, Wiltshite, United Kingdom SN 

16 9SD, telephone: +44 (0) 1666 575111; no 

known Internet address. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64016. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on August 

19, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–20241 Filed 9–2–14; 8:45 am] 

BILLING CODE 4910–13–P 


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