Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Proposed Rules 60667 

Comments Due Date 

(a) We must receive comments by 

November 15, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all McDonnell 

Douglas Corporation Model MD–90–30 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Unsafe Condition 

(e) This AD results from reports of cracks 

found on either the left or right (or in one 

case, both) sides of the center section ribs of 

the horizontal stabilizer. The Federal 

Aviation Administration is issuing this AD to 

detect and correct cracking in the hinge 

bearing lugs of the center section of the left 

and right ribs, which could result in failure 

of the hinge bearing lugs and consequent 

inability of the horizontal stabilizer to sustain 

the required loads. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Repetitive Inspections and Corrective 

Actions for Cracking 

(g) At the applicable time in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin MD90–55A016, Revision 1, dated 

February 17, 2010, except as required by 

paragraph (n) of this AD, do a high frequency 

eddy current (HFEC) inspection for cracking 

on the hinge bearing lugs of the left and right 

sides of the center section ribs of the 

horizontal stabilizer, and do all applicable 

related investigative actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin MD90–55A016, 

Revision 1, dated February 17, 2010. Do all 

applicable related investigative actions before 

further flight. 

(h) If during any inspection required by 

paragraph (g) of this AD, no cracking is 

found, repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed 1,680 flight cycles. 

(i) If during any inspection required by 

paragraph (g) or (h) of this AD, any crack is 

found having a length between Points ‘A’ and 

‘B’ less than or equal to 0.15 inch and crack 

length between Points ‘C’ and ‘D’ less than 

or equal to 0.05 inch, as identified in Boeing 

Alert Service Bulletin MD90–55A016, 

Revision 1, dated February 17, 2010: Before 

further flight, blend out the crack; and within 

1,000 flight cycles after doing the blend out, 

do an HFEC inspection of the blend out on 

the center section rib hinge bearing lug; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–55A016, Revision 1, dated February 

17, 2010. Repeat the HFEC inspection of the 

blend out thereafter at intervals not to exceed 

400 flight cycles until the replacement 

specified by paragraph (j) is done. 

(j) If any cracking is detected during any 

inspection required by paragraph (i) of this 

AD, before further flight, replace the 

horizontal stabilizer center section rib with a 

new horizontal stabilizer center section rib, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–55A016, Revision 1, dated February 

17, 2010. 

(k) If during any inspection required by 

paragraph (g) or (h) of this AD, any crack is 

found having a length between Points ‘A’ and 

‘B’ greater than 0.15 inch or crack length 

between Points ‘C’ and ‘D’ greater than 0.05 

inch, as identified in Boeing Alert Service 

Bulletin MD90–55A016, Revision 1, dated 

February 17, 2010: Before further flight, 

replace the horizontal stabilizer center 

section rib with a new horizontal stabilizer 

center section rib, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–55A016, Revision 1, 

dated February 17, 2010. 

(l) For any airplane having a horizontal 

stabilizer center section rib replaced during 

the actions required by paragraph (j) or (k) of 

this AD: Before the accumulation of 7,200 

total flight cycles on the new horizontal 

stabilizer center section rib, do the actions 

required by paragraph (g) of this AD, and do 

all applicable actions specified in paragraphs 

(h), (i), (j), and (k) of this AD. 

Credit for Actions Accomplished According 

to Previous Issue of Service Bulletin 

(m) Actions accomplished before the 

effective date of this AD according to Boeing 

Alert Service Bulletin MD90–55A016, dated 

December 16, 2009, are considered 

acceptable for compliance with the 

corresponding actions required by 

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

Exceptions to the Service Bulletin 

(n) Where Boeing Alert Service Bulletin 

MD90–55A016, Revision 1, dated February 

17, 2010, specifies a compliance time ‘‘after 

the original issue date on the service 

bulletin,’’ this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) The Manager, Los Angeles ACO, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 627– 

5233; fax (562) 627–5210. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

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. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Issued in Renton, Washington, on 

September 23, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–24715 Filed 9–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0951; Directorate 

Identifier 2010–NM–107–AD] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Model 45 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Model 45 airplanes. This proposed AD 

would require a general visual 

inspection for damage of wiring 

(including chafing, pinched wires, and 

exposed wires) and correct routing of 

wires in the left and right circuit breaker 

panels, and related investigative and 

corrective actions if necessary. This 

proposed AD results from reports of 

wire damage on the pilot and copilot 

circuit breaker panels caused by a short 

circuit between chafed wires. We are 

proposing this AD to detect and correct 

damaged or misrouted wires, which 

could result in a short circuit and the 

loss of systems associated with the 

wiring (including fire suppression 

function for one engine and essential 

avionics systems). 

DATES: We must receive comments on 

this proposed AD by November 15, 

2010. 

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. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
60668 Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Proposed Rules 

• 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 proposed AD, contact Learjet, Inc., 

One Learjet Way, Wichita, Kansas 

67209–2942; telephone 316–946–2000; 

fax 316–946–2220; e-mail 

ac.ict@aero.bombardier.com; Internet 

http://www.bombardier.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington. 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 Management Facility 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 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: 

Kevin Schwemmer, Aerospace Engineer, 

Electrical Systems and Avionics, ACE– 

119W, FAA, Wichita Aircraft 

Certification Office (ACO), 1801 Airport 

Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; 

telephone (316) 946–4174; fax (316) 

946–4107. 

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–2010–0951; Directorate Identifier 

2010–NM–107–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 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 proposed AD. 

Discussion 

We have received reports of a wire 

failure associated with the pilot and 

copilot circuit breaker panel that could 

result in toxic gases in the crew 

compartment. Wire damage caused by a 

short circuit and subsequent burning of 

wires have been reported on four Model 

45 airplanes. In all four incidents, the 

wire damage was associated with the 28 

volts direct current (VDC) power for the 

fire-suppression system. This condition, 

if not corrected, could result in wire 

damage caused by a short circuit, which 

could result in the loss of systems 

associated with the wiring (including 

fire suppression function for one engine 

and essential avionics systems). 

Relevant Service Information 

We have reviewed Bombardier Alert 

Service Bulletin A40–24–11, dated 

November 16, 2009; and Bombardier 

Alert Service Bulletin A45–24–16, dated 

November 16, 2009. The service 

information describes procedures for 

doing a general visual inspection for 

damage of wiring (including chafing, 

pinched wires, and exposed wires) and 

correct routing of wires in the left and 

right circuit breaker panels, and related 

investigative and corrective actions, if 

necessary. The related investigative 

action is doing a general visual 

inspection for arcing damage on the 

mounting brackets of the forward circuit 

breaker panel. Depending on inspection 

findings, the corrective actions are 

replacing damaged (chafed, pinched, or 

exposed) wires, and re-routing any 

incorrectly routed wires; and contacting 

the manufacturer for repair instructions 

and doing the repair. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Service Bulletin.’’ 

Differences Between the Proposed AD 

and Service Bulletin 

Although Bombardier Alert Service 

Bulletin A40–24–11, dated November 

16, 2009; and Bombardier Alert Service 

Bulletin A45–24–16, dated November 

16, 2009; specify that operators may 

contact the manufacturer for disposition 

of certain repair conditions, this 

proposed AD would require operators to 

repair those conditions using a method 

approved by the FAA. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 339 airplanes of U.S. 

registry. We also estimate that it would 

take about 1 work-hour per product to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this proposed AD to the U.S. 

operators to be $28,815, or $85 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), and 

3. 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 190 / Friday, October 1, 2010 / Proposed Rules 60669 

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 adding 

the following new AD: 

Learjet Inc.: Docket No. FAA–2010–0951; 

Directorate Identifier 2010–NM–107–AD. 

Comments Due Date 

(a) We must receive comments by 

November 15, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Learjet Inc. Model 

45 airplanes, certificated in any category; 

having serial numbers identified in 

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

(1) Serial numbers 45–2001 through 45– 

2114 inclusive, 45–2116 through 45–2120 

inclusive, 45–2122, 45–2125, and 45–2126. 

(2) Serial numbers 45–005 through 45–380 

inclusive, 45–382 through 45–391 inclusive, 

45–393 through 45–396 inclusive, 45–398, 

45–400, 45–401, and 45–403. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical power. 

Unsafe Condition 

(e) This AD results from reports of wire 

damage on the pilot and copilot circuit 

breaker panels caused by a short circuit 

between chafed wires. The Federal Aviation 

Administration is issuing this AD to detect 

and correct damaged or misrouted wires, 

which could result in a short circuit and the 

loss of systems associated with the wiring 

(including fire suppression function for one 

engine and essential avionics systems). 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection and Corrective Action 

(g) Within 50 flight hours after the effective 

date of this AD: Do a general visual 

inspection for damage of wiring and correct 

routing of wires in the left and right circuit 

breaker panels, and all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A40–24–11, dated November 16, 

2009; or Bombardier Alert Service Bulletin 

A45–24–16, dated November 16, 2009; as 

applicable; except if arcing damage is found 

on the mounting brackets of the forward 

circuit breaker panel, before further flight, 

repair in accordance with a method approved 

by the Manager, Wichita Aircraft 

Certification Office, FAA. Do all applicable 

related investigative and corrective actions 

before further flight. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Wichita 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. Send information to ATTN: Kevin 

Schwemmer, Aerospace Engineer, Electrical 

Systems and Avionics, ACE–119W, FAA, 

Wichita Aircraft Certification Office (ACO), 

1801 Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; telephone 

(316) 946–4174; fax (316) 946–4107. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Issued in Renton, Washington, on 

September 24, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–24713 Filed 9–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0954; Directorate 

Identifier 2010–NM–078–AD] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation (Type 

Certificate Previously Held by 

Raytheon Aircraft Company; Beech 

Aircraft Corporation) Model 400A and 

400T Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 400A, and 400T airplanes. This 

proposed AD would require a detailed 

inspection for proper sealant of the left 

and right pylon firewall structures, and 

corrective actions if necessary. This 

proposed AD results from reports of 

missing sealant on the left and right 

pylon firewall structures. We are 

proposing this AD to detect and correct 

missing sealant on the left and right 

pylon firewall structures, which, in the 

event of an engine fire, could result in 

flames penetrating the seams in the 

firewall between the engine and the aft 

fuselage, and a subsequent uncontrolled 

fire in the aft fuselage. 

DATES: We must receive comments on 

this proposed AD by November 15, 

2010. 

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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Hawker 

Beechcraft Corporation, Department 62, 

P.O. Box 85, Wichita, Kansas 67201– 

0085; telephone 316–676–8238; fax 

316–676–6706; e-mail 

tmdc@hawkerbeechcraft.com; Internet 

https://www.hawkerbeechcraft.com/ 


jlentini on DSKJ8SOYB1PROD with PROPOSALS