FAA orders · airworthiness directive · current

2011-22-07: Cracks in the front combustion liner

FAA order 2011-22-07 is an airworthiness directive in force since November 29, 2011. The FAA's subject line: Cracks in the front combustion liner. It names the Rolls-Royce RB-211 series, Rolls-Royce RB211-524HT36 engines: about 184 aircraft on the U.S. register today across them, though an order usually covers particular versions or serial numbers rather than every one. System: engine.

What it applies to as the FAA lists it

Kind of product: Engine
Makes: Rolls-Royce plc
Models: RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H-T-36, RB211-524H2-T-19, RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, RB211-Trent 895-17, RB211 Trent 768-60, RB211 Trent 772-60, RB211 Trent 772B-60
Engine series: Rolls-Royce RB-211 series 182 aircraft
Rolls-Royce RB211-524HT36 2 aircraft

Dates and paperwork

In force since: November 29, 2011
Published: October 25, 2011 (signed October 18, 2011)
Docket: FAA-2010-0993
Status: Current
The FAA's document: Read the order on the FAA's site

The FAA's summary their words, unchanged

We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Cracking has been found on the inner wall between intermediate dilution chutes on a total of five front combustion liners of the standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72- D133. The lives of two of these liners were confirmed to be below the currently valid borescope inspection interval. Ultimately, crack propagation could result in hot gas breakout with potential of downstream component distress and multiple turbine blade release beyond containment capabilities of the engine casings. Thus, cracking of this nature constitutes a potentially unsafe condition. Since Rolls-Royce Service Bulletin No. 72-E902 introduces further developments of Rolls-Royce RB211 Service Bulletin No. 72- D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 72-E902 are also considered to be potentially affected and are therefore included in the applicability of this AD. We are issuing this AD to detect cracks in the front combustion liner, which could result in hot section distress, multiple blade release, and possible damage to the airplane.

The order itself the regulatory text, as published

Show the full text (7,279 characters)

Adoption of the Amendment 

	Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 

[[Page 65943]] 

PART 39--AIRWORTHINESS DIRECTIVES 

0 1. The authority citation for part 39 continues to read as follows: 

	Authority: 49 U.S.C. 106(g), 40113, 44701. 

Sec.  39.13  [Amended] 

	2. The FAA amends Sec.  39.13 by adding the following new AD: 

2011-22-07 Rolls-Royce: Amendment 39-16849. Docket No. FAA-2010- 0993; Directorate Identifier 2010-NE-08-AD. 

Effective Date 

	(a) This airworthiness directive (AD) becomes effective November 29, 2011. 

Affected ADs 

	(b) None. 

Applicability 

	(c) This AD applies to Rolls-Royce (RR) turbofan engine models RB211-524G2-T-19, RB211-524G3-T-19, RB211-524H2-T-19, RB211-524H-T- 36, RB211-Trent 768-60, RB211-Trent 772-60, RB211-Trent 772B-60, RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211- Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17 and RB211- Trent 895-17 that incorporate RR Service Bulletin (SB) RB.211-72- D133 or RB.211-72-E902. These engines are installed on, but not limited to, Airbus A330 series airplanes; Boeing 747-400 series, 767 series, and 777 series airplanes. 

Reason 

	(d) This AD results from: 
	Cracking has been found on the inner wall between intermediate dilution chutes on a total of five front combustion liners of the standard corresponding to Rolls-Royce RB211 Service Bulletin No. 72- D133. The lives of two of these liners were confirmed to be below the currently valid borescope inspection interval. Ultimately, crack propagation could result in hot gas breakout with potential of downstream component distress and multiple turbine blade release beyond containment capabilities of the engine casings. Thus, cracking of this nature constitutes a potentially unsafe condition. 
	Since Rolls-Royce Service Bulletin No. 72-E902 introduces further developments of Rolls-Royce RB211 Service Bulletin No. 72- D133, engines incorporating Rolls-Royce RB211 Service Bulletin No. 72-E902 are also considered to be potentially affected and are therefore included in the applicability of this AD. 

	Since EASA issued its AD, another cracking event has occurred, bringing to six the total of crack events of which we are aware. We are issuing this AD to detect cracks in the front combustion liner, which could result in hot section distress, multiple blade release, and possible damage to the airplane. 

Actions and Compliance 

	(e) Unless already done, do the following actions. 

Initial Inspection 

	(f) Perform a borescope inspection of the front combustion liner inner wall, before accumulating the cyclic limits specified in paragraphs (f)(2) and (f)(3) of this AD. 
	(1) If you incorporated paragraph 3.A.(2)(a) of RR Alert Service Bulletin (ASB) RB.211-72-AF458, Revision 4, dated March 9, 2009, or ASB RB.211-72-AF458, Revision 5, dated April 20, 2011, you have satisfied the requirements of paragraph (f) of this AD. 
	(2) If the engine has a combustion liner installed with: 
	(i) A LIFE on the effective date of this AD, that is equal to or greater than the initial inspection threshold specified in column (b) of Table 1 of this AD or a LIFE on the effective date of this AD, that is not known, within 250 cycles after the effective date of this AD, perform a borescope inspection as specified in paragraph (f) of this AD. 
	(ii) A LIFE on the effective date of this AD, that is less than the initial inspection threshold specified in column (b) of Table 1 of this AD, perform the borescope inspection before the LIFE exceeds the limit specified in column (c) of Table 1 of this AD. 

Repeat Inspection 

	(3) Thereafter, repeat the borescope inspection specified in paragraph (f) of this AD at intervals not to exceed the cycles specified in column (d) of Table 1 of this AD. 

	Table 1--Initial Inspection Thresholds and Limits ---------------------------------------------------------------------------------------------------------------- 
	Column (a)                       Column (b)                Column (c)              Column (d) ---------------------------------------------------------------------------------------------------------------- 
	Initial inspection 
	Initial            limit if LIFE is less     Repeat inspection 
	Engine model                  inspectionthreshold        than the initial            interval 
	inspection threshold ---------------------------------------------------------------------------------------------------------------- (i) RB211-524G2-T-19, 524G3-T-19 and  1,150 cycles..............  1,400 cycles..........  1,400 cycles. 
	524H2-T-19. (ii) RB211-524H-T-36................  550 cycles................  800 cycles............  800 cycles. (iii) RB211-Trent 768-60, 772-60 and  1,250 cycles..............  1,500 cycles..........  1,500 cycles. 
	772B-60. (iv) RB211-Trent 892-17, RB211-Trent  750 cycles................  1,000 cycles..........  1,000 cycles. 
	884-17, RB211-Trent 884B-17, RB211- 
	Trent 877-17, RB211-Trent 875-17, 
	RB211-Trent 892B-17 and RB211-Trent 
	895-17 engines. ---------------------------------------------------------------------------------------------------------------- 

Definitions 

	(g) This AD defines LIFE as the lowest of: 
	(1) The number of cycles-since-new of the combustion liner, or 
	(2) The number of cycles-in-service (CIS) since replacement of the inner wall, or 
	(3) The number of CIS since the inner wall of the combustion liner was last borescope-inspected, or inspected by performing paragraph 3.A.(2)(a) of RR ASB RB.211-72-AF458, Revision 4, dated March 9, 2009 or ASB RB.211-72-AF458, Revision 5, dated April 20, 2011. 

FAA AD Differences 

	(h) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) in that the MCAI AD applies to the RB211-Trent 772C-60 engine, which is not type certificated in the United States. The MCAI also allows use of later revisions of the SBs. This AD does not. 

Other FAA AD Provisions 

	(i) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD if requested using the procedures found in 14 CFR 39.19. 

Related Information 

	(j) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009-0243R2, Corrected, dated February 22, 2011, for related information. 
	(k) Rolls-Royce ASB RB.211-72-AF458, Revision 4, dated March 9, 2009, or ASB RB.211-72-AF458, Revision 5, dated April 20, 2011, provide information on how to do the actions required by this AD. For service information identified in this AD, contact Corporate Communications at Rolls-Royce plc, PO Box 31, Derby, DE24 8BJ, United Kingdom, phone: 011-44-1331-242424, fax: 011-44-1332-249936, or e-mail: http://www.rolls-royce.com/contact/civil_team.jsp identifying the correspondence as related to airworthiness directives. 
	(l) Contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: [email protected]; phone: 781-238-7143; fax: 781-238-7199, for more information about this AD. 

Material Incorporated by Reference 

	(m) None. 

[[Page 65944]]

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of November 6, 2026. Connections as data: /graph/directive/2011-22-07.json · aircraft systems.