Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 40065 

(a) Applicability 

This AD applies to Erickson Air-Crane 

Incorporated (Erickson) Model S–64E and S– 

64F helicopters, with rotary wing blade 

assembly (main rotor blade), part number (P/ 

N) 6415–20201–043, –045, –047, –048, –049, 

–050, or –051; or 6415–20601–041, –042, 

–043, –044, –045, –046, –047, –048, –049, 

–050, –051, or –052, installed, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the main rotor blade (blade), which 

could result in blade separation and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 90–26–12, Docket 

No. 90–ASW–27, Amendment 39–6841 (55 

FR 51406, December 14, 1990). 

(d) Comments Due Date 

We must receive comments by September 

3, 2013. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Before further flight, visually check the 

Blade Inspection Method (BIM) pressure 

indicators of the main rotor blades for a black 

or red color indication. 

(2) Before further flight, replace any blade 

with a black or red color indication in a BIM 

pressure indicator with an airworthy part of 

the same part number unless the black or red 

color indication is determined to be the 

result of BIM system malfunction. 

Note 1 to paragraph (f)(2) of this AD: 

Paragraphs (f)(4)(i–iv) of this AD specify how 

to determine if a BIM system is functioning 

correctly. 

(3) Repeat the visual BIM pressure 

indicator check required by paragraph (f)(1) 

of this AD prior to the first flight of each day 

and thereafter at intervals not to exceed: 

(i) Three hours time-in-service (TIS) from 

the last check for helicopters engaged in 

seven or more external lifts per hour; or 

(ii) Five hours TIS from the last check for 

helicopters engaged in either less than seven 

external lifts per hour or operation without 

external cargo. 

(4) Prior to the first flight of each day, 

check the BIM pressure indicator for proper 

function as follows: 

(i) Press in and hold the manual test lever 

(grenade-type handle) on the raised area of 

the handle over the pin-type actuation 

plunger. Do not handle the indicator glass 

bulb since the heat of the hand may change 

the internal reference pressure and result in 

an erroneous indicator reading. 

(ii) Depress the actuation plunger fully to 

shut off the pressure completely from the 

blade into the indicator. If necessary, press 

with the thumbs of both hands to overcome 

the plunger spring force. 

Note 2 to paragraph (f)(4)(ii) of this AD: If 

pressure is applied to the end of the lever on 

the flat area, the actuation plunger will not 

fully depress. 

(iii) Verify proper operation of the 

indicator by observing that a full-black or 

full-red (unsafe) indication appears in not 

less than 10 or more than 30 seconds after 

depressing the plunger for a temperature of 

20 degrees F (¥6.7 degrees C) or above. At 

lower temperatures, extend the upper limit to 

the corresponding time as follows: 

(A) 19 to 0 degrees F (¥7.2 to ¥17.8 

degrees C); upper limit of 35 seconds. 

(B) ¥1 to ¥20 degrees F (¥18.3 to ¥28.9 

degrees C); upper limit of 40 seconds. 

(C) ¥21 to ¥40 degrees F (¥29.4 to ¥40.0 

degrees C); upper limit of 50 seconds. 

(D) ¥41 to ¥60 degrees F (¥40.5 to ¥51.1 

degrees C); upper limit of 60 seconds. 

(iv) Release the lever and observe that the 

black or red indication snaps back 

immediately, leaving an all-white or allyellow (safe) indication. 

(v) If the indicator does not meet the 

specified requirements, then either identify 

and correct the BIM indicator malfunction or 

replace the suspect main rotor blade with an 

airworthy blade of the same part number 

prior to further flight. 

(5) The checks required by paragraphs 

(f)(1) and (f)(4)(i–iv) of this AD may be 

performed by the owner/operator (pilot) 

holding at least a private pilot certificate, and 

must be entered into the aircraft records 

showing compliance with this AD in 

accordance with 14 CFR 43.9 (a)(1)–(4) and 

14 CFR 91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(g) Special Flight Permit 

Special flight permits will not be issued. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: JC Lin, Aviation 

Safety Engineer, Rotorcraft Certification 

Office, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5170; email 7-AVSASW-170@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(i) Additional Information 

Erickson Air-Crane Incorporated Service 

Bulletins No. 64B15–4D, Revision D, dated 

January 26, 2001 for the Model S–64E and 

No. 64F15–2, Revision A, dated July 14, 1999 

for the Model S–64F, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

service information, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson/ 

Compliance Officer, 3100 Willow Springs Rd, 

PO Box 3247, Central Point, OR 97502; 

telephone (541) 664–5544; fax (541) 664– 

2312; email cerickson@ericksonaircrane.com. 

You may review a copy of this information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6210, Main Rotor Blades. 

Issued in Fort Worth, Texas, on June 18, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–15954 Filed 7–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0464; Directorate 

Identifier 2012–NM–010–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Dassault Aviation 

Model FALCON 7X airplanes. The 

existing AD currently requires adding 

an automatic reversion logic and a 

means for the pilot to override pitch 

trim control normal modes, and 

installing placards in the cockpit; 

replacing the frame of the emergency 

switch box; replacing certain horizontal 

stabilizer electronic control units 

(HSECU); operating the airplane 

according to the limitations and 

procedures in the airplane flight manual 

(AFM); revising the Limitations section 

of the AFM; and revising the 

maintenance program to incorporate a 

certain maintenance planning document 

(MPD) task. Since we issued that AD, 

Dassault Aviation has developed a 

modification of the fly-by-wire (FBW) 

standard; changed the AFM to 

incorporate changes resulting from the 

FBW modification; and revised the 

airplane maintenance manual (AMM) to 

incorporate repetitive operational tests 

of the electric motors reversion relays 

and trim emergency command of the 

horizontal stabilizer trim system 

(HSTS). Once incorporated, these 

actions allow restoration of the 

originally certified minimum equipment 

list items. This proposed AD would 

retain certain requirements of the 

previous AD; would require modifying 

the FBW standard; operating the 


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airplane according to the limitations 

and procedures in an approved AFM; 

and operational testing of the electric 

motors reversion relays and trim 

emergency command of the HSTS, and 

repairs if necessary. We are proposing 

this AD to prevent an uncontrolled 

pitch trim runaway, which could result 

in loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 19, 2013. 

ADDRESSES: You may send comments 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Dassault 

Falcon Jet, P.O. Box 2000, South 

Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet 

http://www.dassaultfalcon.com. 

You may review copies of the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0464; Directorate Identifier 

2012–NM–010–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

On July 15, 2011, we issued AD 2011– 

16–01, Amendment 39–16759 (76 FR 

47424, August 5, 2011). That AD 

requires actions intended to address an 

unsafe condition on all Dassault 

Aviation Model FALCON 7X airplanes. 

Since we issued AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, 

August 5, 2011), the European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2011– 

0241, dated December 19, 2011 (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

In May 2011, a Dassault Aviation Falcon 

7X aeroplane experienced an uncontrolled 

pitch trim runaway during descent. The crew 

succeeded in recovering a stable situation 

and performed an uneventful landing. 

The results of the investigations showed 

that there was a production defect in the 

Horizontal Stabilizer Electronic Control Unit 

(HSECU) which could have contributed to 

the cause of the event. 

This condition, if not corrected, could lead 

to a loss of control of the aeroplane. 

To address this unsafe condition, EASA 

issued emergency AD 2011–0102–E which 

prohibited further flights. Following further 

technical investigations accomplished by 

Dassault Aviation, EASA issued AD 2011– 

0114, currently at revision 2, which 

superseded EASA AD 2011–0102–E. 

Following accomplishment of all the actions 

as required by EASA AD 2011–0114R2, all 

aeroplanes could resume flying with 

operational limitations. 

Since EASA AD 2011–0114R2 was issued, 

Dassault Aviation have developed a 

modification (M1245 to be embodied through 

accomplishment of Dassault Aviation Service 

Bulletin F7X–214) of the Fly-By-Wire (FBW) 

current standard which improves the 

monitoring and reversion logic of the 

Horizontal Stabilizer Trim System (HSTS). 

This modification results in earlier failure 

detection and quicker reversion. 

Dassault Aviation have issued as well 

Revision 13 of the Aircraft Flight Manual 

(AFM) which incorporates the changes 

introduced in EASA AD 2011–0114R2 (CP55 

and 56) as well as the new changes resulting 

from Dassault Aviation M1245 (CP58). 

Dassault Aviation have introduced as well 

operational tests of the HSTS electric motors 

reversion relays and of the HSTS trim 

emergency command into the Chapter 5.40 of 

F7X Aircraft Maintenance Manual (CP010). 

For the reasons described above, EASA 

issued AD 2011–0169 to require: 

1. accomplishing Dassault Aviation 

modification M1245, 

2. amending the AFM, and 

3. implementing the operational tests of the 

HSTS electric motors reversion relays and of 

the HSTS trim emergency command. 

Accomplishment of all the above actions 

restored the full original certified flight 

envelope of the aeroplane. 

Since EASA AD 2011–0169 was issued, 

further analyses have demonstrated that, 

once Dassault Aviation modification M1245 

is embodied, it is allowed to restore the 

originally certified Minimum Equipment List 

(MEL) items which were removed in 

accordance with the requirement of 

paragraph (4) of EASA AD 2011–0114R2. 

For the reasons described above, this 

[EASA] AD, which supersedes EASA AD 

2011–0169, retaining its requirements, in 

addition, extends the applicability of the AD 

to all S/Ns and, for aeroplanes fitted with 

FBW standard 2.1.7.3, allows the MEL 

limitations imposed by EASA AD 2011– 

0114R2 to be removed. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Dassault has issued the following 

service information. 

• Dassault Mandatory Service 

Bulletin 7X–214, including New 

Standard Installation Checklist, dated 

August 30, 2011. 

• Dassault Mandatory Service 

Bulletin 7X–214, Revision Erratum, 

dated January 26, 2012. 

• Dassault Falcon 7X AFM, Revision 

13, dated August 29, 2011. 

• FCS Data Loading Procedure, 

Reference DT EQUIP 43913, Issue D, 

dated May 28, 2010. 

• Chapter 5–40–00, Airworthiness 

Limitations, of the Falcon 7X 

Maintenance Manual DGT 107838, 

Revision 2, dated August 25, 2011. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

Explanation of Changes Made to This 

NPRM 

We have revised the heading and 

wording for paragraph (h) of this 


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proposed AD; this change does not 

affect the intent of that paragraph. 

We have deleted note 2 to paragraph 

(l) of AD 2011–16–01, Amendment 39– 

16759 (76 FR 47424, August 5, 2011). 

Instead, we have included that 

information in paragraph (l)(2) of this 

proposed AD. 

We have deleted note 3 of AD 2011– 

16–01, Amendment 39–16759 (76 FR 

47424, August 5, 2011). Instead, we 

have included that information in 

paragraph (n) of this proposed AD. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This AD requires revisions to certain 

operator maintenance documents to 

include new inspections. Compliance 

with these inspections is required by 14 

CFR 91.403(c). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by these 

inspections, the operator may not be 

able to accomplish the inspections 

described in the revisions. In this 

situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance according to the procedures 

specified in paragraph (s) of this 

proposed AD. The request should 

include a description of changes to the 

required inspections that will ensure the 

continued operational safety of the 

airplane. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 30 products of U.S. registry. 

The actions that are required by AD 

2011–16–01, Amendment 39–16759 (76 

FR 47424, August 5, 2011), and retained 

in this proposed AD take about 340 

work-hours per product, at an average 

labor rate of $85 per work hour. Where 

the service information lists required 

parts costs that are covered under 

warranty, we have assumed that there 

will be no charge for these parts. As we 

do not control warranty coverage for 

affected parties, some parties may incur 

costs higher than estimated here. Based 

on these figures, the estimated cost of 

the currently required actions is $28,900 

product. 

We estimate that it would take about 

11 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$28,050, or $935 per product. 

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 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing airworthiness directive (AD) 

2011–16–01, Amendment 39–16759 (76 

FR 47424, August 5, 2011), and adding 

the following new AD: 

Dassault Aviation: Docket No. FAA–2013– 

0464; Directorate Identifier 2012–NM– 

010–AD. 

(a) Comments Due Date 

We must receive comments by August 19, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). 

(c) Applicability 

This AD applies to all Dassault Aviation 

Model FALCON 7X airplanes, certificated in 

any category, all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by an uncontrolled 

pitch trim runaway during descent. We are 

issuing this AD to prevent an uncontrolled 

pitch trim runaway, which could result in 

loss of control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Modification 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–16–01, 

Amendment 39–16759 (76 FR47424, August 

5, 2011). Before further flight, do the 

applicable actions specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD. 

(1) For airplanes on which Dassault 

Mandatory Service Bulletin 7X–211, Revision 

1, dated June 14, 2011, has not been done as 


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of August 22, 2011 (the effective date of AD 

2011–16–01, Amendment 39–16759 (76 FR 

47424, August 5, 2011)): Modify the airplane 

by adding an automatic reversion logic and 

a means for the pilot to override pitch trim 

control normal modes, and install placards in 

the cockpit in full view of the pilots, in 

accordance with paragraph 2., 

‘‘Accomplishment Instructions for Aircraft 

which have not Already Implemented the 

Revision 1 of the Service Bulletin,’’ of 

Dassault Mandatory Service Bulletin 7X–211, 

Revision 2, including New Standard 

Installation Checklist and Appendix A, dated 

June 22, 2011, including FCS Data Loading 

Procedure, Issue D, dated May 28, 2010. 

(2) For airplanes on which Dassault 

Mandatory Service Bulletin 7X–211, Revision 

1, dated June 14, 2011, has been done as of 

August 22, 2011 (the effective date of AD 

2011–16–01, Amendment 39–16759 (76 FR 

47424, August 5, 2011)): Replace the frame of 

the emergency switch box, in accordance 

with paragraph 3., ‘‘Accomplishment 

Instructions for Aircraft which have Already 

Implemented Revision 1 of this Service 

Bulletin,’’ of Dassault Mandatory Service 

Bulletin 7X–211, Revision 2, including New 

Standard Installation Checklist and 

Appendix A, dated June 22, 2011, including 

FCS Data Loading Procedure, Issue D, dated 

May 28, 2010. 

(3) For airplanes equipped with any 

horizontal stabilizer electronic control unit 

(HSECU) P/N 051244–04, replace the HSECU 

with any HSECU identified in paragraph 

(g)(3)(i), (g)(3)(ii), or (g)(3)(iii) of this AD, in 

accordance with the Accomplishment 

Instructions of Dassault Mandatory Service 

Bulletin 7X–212, Revision 2, dated July 7, 

2011. 

(i) HSECU P/N 051244–02. 

(ii) Verified HSECU P/N 051244–04 having 

a stamped ‘‘V.’’ 

(iii) HSECU P/N 051244–05. 

(h) Retained Credit for Previous Actions 

This paragraph restates the provisions 

specified in paragraph (h) of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). This paragraph provides credit for 

the HSECU replacement required by 

paragraph (g)(3)(i) or (g)(3)(ii) of this AD, if 

those replacements were performed before 

August 22, 2011 (the effective date of AD 

2011–16–01), using Dassault Mandatory 

Service Bulletin 7X–212, Revision 1, dated 

June 23, 2011, which is not incorporated by 

reference in this AD. 

(i) Retained Revision of Airplane Flight 

Manual (AFM) 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–16–01, Amendment 

39–16759 (76 FR 47424, August 5, 2011). As 

of August 22, 2011 (the effective date AD 

2011–16–01), operate the airplane according 

to the limitations and procedures in the 

Dassault Falcon 7X AFM, Revision 12, dated 

June 16, 2011, until the actions required by 

paragraph (p) of this AD are accomplished. 

Revision 12 introduces revised operational 

speed limitations and revised procedures 

accounting for the new TRIM EMERG button. 

(j) Retained Electronic Checklist Database 

Installation 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–16–01, Amendment 

39–16759 (76 FR 47424, August 5, 2011). 

Before further flight, install the electronic 

checklist V0007 database, in accordance with 

the Accomplishment Instructions of Dassault 

Service Bulletin 7X–213, dated June 22, 

2011. Accomplishment of the actions 

required in paragraph (o) of this AD 

terminates the actions required by paragraph 

(j) of this AD. 

(k) Retained Operating Restrictions 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). Before further flight, revise the 

Limitations section of the Dassault Falcon 7X 

AFM to include the information provided in 

Figure 1 to paragraph (k) of this AD. This 

may be accomplished by inserting a copy of 

Figure 1 to paragraph (k) of this AD into the 

AFM. Accomplishment of the actions 

required in paragraph (p) of this AD 

terminates the actions required by paragraph 

(k) of this AD. 

Figure 1 to Paragraph (k) of This AD 

Dispatch with any inoperative equipment 

identified below is prohibited. This 

prohibition takes precedence over the FAA 

master minimum equipment list (MMEL) or 

any operator’s MEL. 

Air data systems (identified as MEL item 34– 

9) 

Multi functional probe (MFP) heating system 

(identified as MMEL item 30–1) 

ACMU3 and ACMU4 (identified as MMEL 

item 27–3) 

LH REAR POWER #3 (identified as MMEL 

item 27–5–(–6) 

Back-up mode (identified as MMEL item 27– 

8) 

(l) Retained Maintenance Program Revision 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–16–01, Amendment 

39–16759 (76 FR 47424, August 5, 2011). 

(1) Within 30 days after August 22, 2011 

(the effective date of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011)), revise the maintenance program to 

incorporate Maintenance Planning Document 

(MPD) Task 27–40–00–710–801, as specified 

in Dassault Aviation, Falcon 7X Maintenance 

Manual (MM), Falcon 7X—Chapter 5–40–00 

after Rev 01, dated June 10, 2011 (commonly 

referred to as Dassault Change Proposal (CP) 

CP009 to Chapter 5–40–00 of Dassault Falcon 

7X MM). The initial compliance time for 

doing the operational test of the HSTS 

electric motors reversion relays is 1,850 flight 

hours after accomplishment of the applicable 

actions required by paragraph (g) of this AD. 

Accomplishment of the actions required in 

paragraph (q) of this AD terminates the 

actions required by paragraph (l) of this AD. 

(2) The MM revision required by paragraph 

(l) of this AD may be done by inserting a 

copy of Dassault CP CP009, dated June 10, 

2011, to Chapter 5–40–00 of Dassault Falcon 

7X MM into the MM. When Dassault CP 

CP009 has been included in general revisions 

of the MM, the general revisions may be 

inserted into the MM, provided the relevant 

information in the general revision is 

identical to that in Dassault CP CP009, and 

Dassault CP CP009 may be removed. 

(m) Retained Limitations for Alternative 

Procedures or Intervals 

This paragraph restates the requirements of 

paragraph (m) of AD 2011–16–01, 

Amendment 39–16759 (76 FR47424, August 

5, 2011). After the maintenance program has 

been revised as required by paragraph (l) of 

this AD, no alternative procedure or interval 

for the operational test may be used unless 

the procedure and/or interval is approved as 

an alternative method of compliance (AMOC) 

in accordance with the procedures specified 

in paragraph (s) of this AD. 

(n) Retained FAA AD Differences 

This paragraph restates the AD differences 

identified by Note 3 of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). This AD differs from the mandatory 

continuing airworthiness information (MCAI) 

and/or service information as follows: 

(1) European Aviation Safety Agency 

(EASA) AD 2011–0114R2 requires repetitive 

operational tests of the HSTS electric motors 

reversion relays, and specifies that the 

aircraft maintenance program may be revised 

in lieu of those repetitive tests. This FAA AD 

mandates revising the maintenance program. 

(2) EASA AD 2011–0114R2 does not 

include any requirement to revise the 

electronic checklist. Paragraph (j) of this FAA 

AD requires this action. 

(3) EASA AD 2011–0114R2 mandates 

amending the minimum equipment list 

(MEL) by removing certain items. This FAA 

AD instead requires revising the AFM to 

prohibit dispatch with those items 

inoperative. The operational effect, however, 

is the same. 

(o) New Fly-By-Wire System Modification 

Within 12 months after accomplishing the 

actions required by paragraph (g) of this AD 

or within 9 months after the effective date of 

this AD, whichever is later: Modify the flyby-wire system installed in the airplane to 

the 2.1.7.3 standard, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–214, dated 

August 30, 2011, as revised by Dassault 

Mandatory Service Bulletin 7X–214, Revision 

Erratum, dated January 26, 2012. 

Accomplishment of the actions required in 

paragraph (o) of this AD terminates the 

actions required by paragraph (j) of this AD. 

(p) New AFM Revision 

After accomplishing the actions required 

by paragraph (o) of this AD: Operate the 

airplane thereafter according to the 

limitations and procedures specified in 

Dassault Falcon 7X AFM, Revision 13, dated 

August 29, 2011. Accomplishment of the 

actions required by this paragraph terminates 

the requirements of paragraphs (i) and (k) of 

this AD; thereafter, the AFM limitation 

required by paragraph (k) of this AD may be 

removed from the AFM. 

(q) New Maintenance Program Revision 

Within 30 days after the effective date of 

this AD: Revise the maintenance program to 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 40069 

incorporate Chapter 5–40–00, Airworthiness 

Limitations, of the Dassault Falcon 7X MM 

DGT 107838, Revision 2, dated August 25, 

2011, into the MM. 

(1) The initial compliance time for the 

operational test of the HSTS trim emergency 

command is within 650 flight hours after the 

modification required by paragraph (o) of this 

AD. 

(2) The initial compliance time for the 

operational test of the HSTS electric motors 

reversion relays is within 5,050 flight hours 

after the modification required by paragraph 

(o) of this AD. 

(3) Accomplishment of the actions required 

in paragraph (q) of this AD terminates the 

actions required by paragraph (l) of this AD. 

(r) New Limitations for Alternative Actions 

or Intervals 

After accomplishing the revision required 

by paragraph (q) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (s) of 

this AD. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, Transport Airplane Directorate, 

ANM–116, 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: 

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. 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. AMOCs approved previously in 

accordance with AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011), are approved as AMOCs for the 

corresponding provisions of this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(t) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0241, dated December 19, 

2011, and the service information specified 

in paragraphs (t)(1)(i) though (t)(1)(ix) of this 

AD. 

(i) Chapter 5–40–00, Airworthiness 

Limitations, of the Dassault Falcon 7X MM 

DGT 107838, Revision 2, dated August 25, 

2011. 

(ii) Dassault Change Proposal CP009 to 

Chapter 5–40- 00 of Dassault Falcon 7X 

Maintenance Manual), dated June 10, 2011. 

(iii) Dassault Falcon 7X Airplane Flight 

Manual, Revision 12, dated June 16, 2011. 

(iv) Dassault Falcon 7X Airplane Flight 

Manual, Revision 13, dated August 29, 2011. 

(v) Dassault Mandatory Service Bulletin 

7X–211, Revision 2, including New Standard 

Installation Checklist and Appendix A, dated 

June 22, 2011, including FCS Data Loading 

Procedure, Issue D, dated May 28, 2010. 

(vi) Dassault Mandatory Service Bulletin 

7X–212, Revision 2, dated July 7, 2011. 

(vii) Dassault Mandatory Service Bulletin 

7X–214, dated August 30, 2011. 

(viii) Dassault Mandatory Service Bulletin 

7X–214, Revision Erratum, dated January 26, 

2012. 

(ix) Dassault Service Bulletin 7X–213, 

dated June 22, 2011. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. You may review 

copies of the 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. 

Issued in Renton, Washington, on June 14, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–15949 Filed 7–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0539; Directorate 

Identifier 2012–NM–145–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of Proposed Rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2000–12– 

11, that applies to certain Model A300 

B4–600 and Model A300 B4–600R series 

airplanes. That AD currently requires 

repetitive inspections to detect cracks in 

the bolt holes inboard and outboard of 

rib 9 on the bottom booms of the front 

and rear wing spars, and repair if 

necessary. Since we issued that AD, we 

have determined through a fleet survey 

and an updated fatigue and damage 

tolerance analysis that the risk for 

fatigue cracking on the front and rear 

spar bottom booms is higher than was 

initially determined. This proposed AD 

would reduce the initial inspection 

compliance time and repetitive 

inspection interval. We are proposing 

this AD to detect and correct fatigue 

cracks in the bolt holes of the wing 

spars, which could result in reduced 

structural integrity of a wing spar. 

DATES: We must receive comments on 

this proposed AD by August 19, 2013. 

ADDRESSES: You may send comments 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 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. You 

may review copies of the 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 227–2125; 

fax: (425) 227–1149. 


tkelley on DSK3SPTVN1PROD with PROPOSALS